RAF 89 AIRFOIL (raf89-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 89 AIRFOIL (raf89-il) Reynolds number: 1,000,000 Max Cl/Cd: 45.6 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf89-il-1000000-n5.txt Download as CSV file: xf-raf89-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 89 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.0190 0.08236 0.07789 -0.0718 1.0000 0.0598
-19.500 -1.0300 0.07826 0.07375 -0.0730 1.0000 0.0607
-19.250 -1.0356 0.07489 0.07032 -0.0739 1.0000 0.0613
-19.000 -1.0425 0.07143 0.06681 -0.0747 1.0000 0.0619
-18.750 -1.0490 0.06804 0.06337 -0.0754 1.0000 0.0626
-18.500 -1.0534 0.06496 0.06023 -0.0759 1.0000 0.0633
-18.250 -1.0564 0.06208 0.05730 -0.0763 1.0000 0.0639
-18.000 -1.0592 0.05927 0.05443 -0.0767 1.0000 0.0646
-17.750 -1.0496 0.05635 0.05146 -0.0792 0.9994 0.0654
-17.500 -1.0377 0.05352 0.04858 -0.0819 0.9984 0.0663
-17.250 -1.0414 0.05066 0.04569 -0.0813 0.9884 0.0673
-17.000 -1.0366 0.04801 0.04300 -0.0826 0.9806 0.0683
-16.750 -1.0214 0.04560 0.04054 -0.0852 0.9628 0.0695
-16.500 -0.9882 0.04304 0.03791 -0.0914 0.9410 0.0713
-16.250 -0.9507 0.04065 0.03536 -0.0982 0.9022 0.0736
-16.000 -0.9314 0.03859 0.03310 -0.1013 0.8610 0.0756
-15.750 -0.9155 0.03694 0.03130 -0.1031 0.8354 0.0775
-15.500 -0.9002 0.03536 0.02961 -0.1045 0.8174 0.0793
-15.250 -0.8853 0.03372 0.02790 -0.1060 0.8049 0.0814
-15.000 -0.8686 0.03210 0.02622 -0.1078 0.7939 0.0842
-14.750 -0.8451 0.03077 0.02482 -0.1103 0.7849 0.0867
-14.500 -0.8286 0.02927 0.02329 -0.1118 0.7769 0.0894
-14.250 -0.8114 0.02797 0.02194 -0.1130 0.7685 0.0930
-14.000 -0.7942 0.02678 0.02069 -0.1140 0.7608 0.0960
-13.750 -0.7804 0.02551 0.01941 -0.1145 0.7545 0.0997
-13.500 -0.7641 0.02446 0.01832 -0.1150 0.7483 0.1031
-13.250 -0.7494 0.02338 0.01721 -0.1153 0.7423 0.1067
-13.000 -0.7350 0.02239 0.01620 -0.1152 0.7374 0.1107
-12.750 -0.7200 0.02150 0.01529 -0.1150 0.7334 0.1142
-12.500 -0.7075 0.02053 0.01432 -0.1146 0.7287 0.1189
-12.250 -0.6928 0.01976 0.01353 -0.1140 0.7235 0.1231
-12.000 -0.6799 0.01896 0.01271 -0.1132 0.7184 0.1274
-11.750 -0.6666 0.01824 0.01198 -0.1123 0.7143 0.1324
-11.500 -0.6525 0.01757 0.01131 -0.1113 0.7113 0.1366
-11.250 -0.6402 0.01688 0.01063 -0.1101 0.7078 0.1418
-11.000 -0.6259 0.01632 0.01006 -0.1089 0.7042 0.1472
-10.750 -0.6132 0.01574 0.00948 -0.1074 0.7004 0.1513
-10.500 -0.6004 0.01523 0.00895 -0.1058 0.6961 0.1570
-10.250 -0.5859 0.01479 0.00850 -0.1044 0.6921 0.1609
-10.000 -0.5732 0.01429 0.00802 -0.1026 0.6897 0.1664
-9.750 -0.5581 0.01390 0.00763 -0.1011 0.6869 0.1711
-9.500 -0.5435 0.01353 0.00726 -0.0994 0.6838 0.1752
-9.250 -0.5296 0.01316 0.00690 -0.0975 0.6803 0.1797
-9.000 -0.5150 0.01285 0.00658 -0.0956 0.6768 0.1847
-8.750 -0.4998 0.01259 0.00629 -0.0937 0.6729 0.1885
-8.500 -0.4867 0.01228 0.00599 -0.0915 0.6694 0.1939
-8.250 -0.4701 0.01203 0.00575 -0.0898 0.6666 0.1982
-8.000 -0.4533 0.01182 0.00553 -0.0880 0.6620 0.2018
-7.750 -0.4389 0.01157 0.00529 -0.0858 0.6571 0.2065
-7.500 -0.4245 0.01137 0.00507 -0.0835 0.6520 0.2120
-7.250 -0.4083 0.01120 0.00489 -0.0815 0.6478 0.2174
-7.000 -0.3939 0.01095 0.00468 -0.0792 0.6450 0.2245
-6.750 -0.3766 0.01077 0.00452 -0.0773 0.6419 0.2307
-6.500 -0.3601 0.01060 0.00435 -0.0753 0.6380 0.2357
-6.250 -0.3440 0.01044 0.00420 -0.0731 0.6343 0.2407
-6.000 -0.3267 0.01032 0.00406 -0.0711 0.6300 0.2455
-5.750 -0.3090 0.01022 0.00394 -0.0692 0.6263 0.2497
-5.500 -0.2924 0.01006 0.00381 -0.0670 0.6233 0.2549
-5.250 -0.2746 0.00994 0.00371 -0.0650 0.6192 0.2605
-5.000 -0.2562 0.00988 0.00364 -0.0631 0.6151 0.2648
-4.750 -0.2411 0.00980 0.00356 -0.0606 0.6106 0.2701
-4.500 -0.2266 0.00975 0.00350 -0.0579 0.6060 0.2755
-4.250 -0.2069 0.00968 0.00345 -0.0562 0.6023 0.2805
-4.000 -0.1856 0.00962 0.00338 -0.0549 0.5977 0.2843
-3.750 -0.1664 0.00954 0.00331 -0.0531 0.5924 0.2899
-3.500 -0.1468 0.00949 0.00325 -0.0515 0.5871 0.2952
-3.250 -0.1245 0.00944 0.00320 -0.0503 0.5827 0.3002
-3.000 -0.1025 0.00938 0.00315 -0.0491 0.5777 0.3047
-2.750 -0.0823 0.00932 0.00309 -0.0475 0.5713 0.3108
-2.500 -0.0617 0.00930 0.00305 -0.0460 0.5651 0.3165
-2.250 -0.0385 0.00926 0.00302 -0.0450 0.5595 0.3211
-2.000 -0.0177 0.00921 0.00297 -0.0435 0.5526 0.3269
-1.750 0.0022 0.00919 0.00294 -0.0419 0.5456 0.3335
-1.500 0.0246 0.00916 0.00291 -0.0407 0.5382 0.3391
-1.250 0.0445 0.00916 0.00289 -0.0391 0.5294 0.3452
-1.000 0.0650 0.00913 0.00286 -0.0375 0.5219 0.3517
-0.750 0.0850 0.00913 0.00285 -0.0359 0.5122 0.3582
-0.500 0.1044 0.00914 0.00285 -0.0342 0.5030 0.3648
-0.250 0.1226 0.00913 0.00283 -0.0322 0.4931 0.3729
0.000 0.1409 0.00916 0.00284 -0.0302 0.4838 0.3798
0.250 0.1586 0.00918 0.00284 -0.0281 0.4740 0.3863
0.500 0.1714 0.00917 0.00283 -0.0250 0.4649 0.3952
0.750 0.1856 0.00919 0.00284 -0.0222 0.4555 0.4035
1.000 0.1984 0.00919 0.00284 -0.0192 0.4471 0.4144
1.500 0.2274 0.00922 0.00291 -0.0138 0.4311 0.4414
1.750 0.2420 0.00920 0.00297 -0.0112 0.4247 0.4634
2.000 0.2570 0.00920 0.00305 -0.0087 0.4183 0.4876
2.250 0.2702 0.00931 0.00318 -0.0058 0.4105 0.5072
2.500 0.2883 0.00938 0.00328 -0.0039 0.4051 0.5225
2.750 0.3059 0.00947 0.00340 -0.0019 0.3994 0.5321
3.000 0.3221 0.00963 0.00353 0.0003 0.3929 0.5403
3.250 0.3403 0.00976 0.00366 0.0021 0.3881 0.5452
3.500 0.3585 0.00987 0.00378 0.0039 0.3826 0.5509
3.750 0.3754 0.01003 0.00393 0.0059 0.3768 0.5568
4.000 0.3908 0.01024 0.00411 0.0082 0.3710 0.5610
4.250 0.4109 0.01037 0.00424 0.0095 0.3670 0.5641
4.500 0.4283 0.01053 0.00440 0.0114 0.3615 0.5680
4.750 0.4434 0.01074 0.00461 0.0136 0.3560 0.5720
5.000 0.4597 0.01096 0.00481 0.0155 0.3513 0.5755
5.250 0.4783 0.01113 0.00500 0.0171 0.3473 0.5785
5.500 0.4957 0.01135 0.00521 0.0187 0.3425 0.5814
5.750 0.5110 0.01165 0.00547 0.0207 0.3367 0.5841
6.000 0.5270 0.01194 0.00574 0.0225 0.3324 0.5859
6.250 0.5451 0.01214 0.00597 0.0240 0.3285 0.5900
6.500 0.5617 0.01240 0.00625 0.0257 0.3241 0.5938
6.750 0.5761 0.01275 0.00659 0.0276 0.3189 0.5973
7.000 0.5918 0.01309 0.00693 0.0293 0.3143 0.6006
7.250 0.6094 0.01340 0.00724 0.0307 0.3103 0.6037
7.500 0.6266 0.01374 0.00758 0.0320 0.3061 0.6062
7.750 0.6423 0.01414 0.00797 0.0336 0.3017 0.6088
8.000 0.6562 0.01459 0.00843 0.0353 0.2970 0.6131
8.250 0.6747 0.01491 0.00878 0.0363 0.2934 0.6170
8.500 0.6911 0.01534 0.00922 0.0376 0.2886 0.6213
8.750 0.7060 0.01585 0.00973 0.0390 0.2838 0.6259
9.000 0.7222 0.01634 0.01022 0.0402 0.2796 0.6297
9.250 0.7398 0.01678 0.01070 0.0411 0.2755 0.6354
9.500 0.7566 0.01729 0.01122 0.0420 0.2707 0.6401
9.750 0.7716 0.01791 0.01184 0.0431 0.2653 0.6448
10.000 0.7893 0.01846 0.01241 0.0438 0.2620 0.6497
10.500 0.8249 0.01964 0.01365 0.0448 0.2516 0.6657
11.000 0.8629 0.02100 0.01511 0.0449 0.2401 0.6963
11.250 0.8818 0.02190 0.01606 0.0444 0.2319 0.7214
11.500 0.9067 0.02267 0.01693 0.0430 0.2250 0.7502
11.750 0.9316 0.02362 0.01794 0.0413 0.2184 0.7758
12.000 0.9683 0.02434 0.01876 0.0378 0.2142 0.7996
12.250 1.0006 0.02519 0.01971 0.0348 0.2086 0.8272
12.500 1.0345 0.02623 0.02093 0.0311 0.2033 0.8772
12.750 1.1240 0.02739 0.02229 0.0168 0.1959 0.9600
13.000 1.1485 0.02870 0.02358 0.0148 0.1904 0.9902
13.250 1.1537 0.02995 0.02483 0.0173 0.1865 0.9990
13.500 1.1774 0.03121 0.02609 0.0156 0.1818 1.0000
13.750 1.1852 0.03249 0.02736 0.0167 0.1770 1.0000
14.000 1.1950 0.03367 0.02854 0.0176 0.1734 1.0000
14.250 1.2036 0.03498 0.02986 0.0185 0.1688 1.0000
14.500 1.2101 0.03644 0.03130 0.0195 0.1636 1.0000
14.750 1.2179 0.03788 0.03274 0.0203 0.1596 1.0000
15.000 1.2262 0.03929 0.03416 0.0210 0.1553 1.0000
15.250 1.2299 0.04109 0.03594 0.0219 0.1497 1.0000
15.500 1.2369 0.04268 0.03755 0.0226 0.1454 1.0000
15.750 1.2426 0.04437 0.03923 0.0232 0.1407 1.0000
16.000 1.2454 0.04636 0.04123 0.0239 0.1364 1.0000
16.250 1.2506 0.04818 0.04305 0.0244 0.1314 1.0000
16.500 1.2501 0.05054 0.04541 0.0250 0.1267 1.0000
16.750 1.2559 0.05237 0.04726 0.0253 0.1227 1.0000
17.000 1.2543 0.05492 0.04981 0.0258 0.1178 1.0000
17.250 1.2576 0.05703 0.05194 0.0260 0.1141 1.0000
17.500 1.2554 0.05974 0.05465 0.0263 0.1092 1.0000
17.750 1.2549 0.06231 0.05724 0.0264 0.1054 1.0000
18.000 1.2539 0.06499 0.05994 0.0265 0.1014 1.0000
18.250 1.2500 0.06799 0.06296 0.0265 0.0979 1.0000
18.500 1.2504 0.07059 0.06559 0.0264 0.0947 1.0000
18.750 1.2471 0.07364 0.06868 0.0262 0.0916 1.0000
19.000 1.2443 0.07667 0.07172 0.0260 0.0886 1.0000
19.250 1.2422 0.07967 0.07477 0.0256 0.0864 1.0000
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