RAF 89 AIRFOIL (raf89-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 89 AIRFOIL (raf89-il) Reynolds number: 500,000 Max Cl/Cd: 39.68 at α=11.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf89-il-500000-n5.txt Download as CSV file: xf-raf89-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.250 -0.9225 0.08777 0.08261 -0.0716 1.0000 0.0718
-19.000 -0.9241 0.08474 0.07953 -0.0725 1.0000 0.0726
-18.750 -0.9303 0.08118 0.07595 -0.0736 1.0000 0.0736
-18.500 -0.9352 0.07784 0.07256 -0.0744 1.0000 0.0747
-18.250 -0.9402 0.07451 0.06920 -0.0753 1.0000 0.0758
-18.000 -0.9427 0.07155 0.06619 -0.0759 1.0000 0.0772
-17.750 -0.9451 0.06864 0.06323 -0.0764 1.0000 0.0785
-17.500 -0.9465 0.06589 0.06043 -0.0768 1.0000 0.0796
-17.250 -0.9530 0.06264 0.05715 -0.0773 1.0000 0.0810
-17.000 -0.9579 0.05965 0.05413 -0.0775 1.0000 0.0823
-16.750 -0.9608 0.05695 0.05139 -0.0776 1.0000 0.0838
-16.500 -0.9617 0.05451 0.04889 -0.0776 1.0000 0.0853
-16.250 -0.9458 0.05171 0.04605 -0.0808 0.9984 0.0875
-16.000 -0.9441 0.04867 0.04299 -0.0814 0.9865 0.0894
-15.750 -0.9350 0.04613 0.04041 -0.0831 0.9743 0.0917
-15.500 -0.9168 0.04385 0.03808 -0.0860 0.9565 0.0946
-15.250 -0.8916 0.04112 0.03530 -0.0912 0.9385 0.0977
-15.000 -0.8562 0.03869 0.03280 -0.0976 0.9190 0.1027
-14.750 -0.8185 0.03631 0.03032 -0.1046 0.8963 0.1073
-14.500 -0.7774 0.03436 0.02825 -0.1115 0.8753 0.1124
-14.250 -0.7491 0.03253 0.02630 -0.1159 0.8541 0.1172
-13.750 -0.7118 0.02972 0.02331 -0.1195 0.8220 0.1262
-13.500 -0.6975 0.02843 0.02194 -0.1202 0.8095 0.1311
-13.000 -0.6725 0.02617 0.01956 -0.1203 0.7890 0.1400
-12.750 -0.6598 0.02518 0.01853 -0.1200 0.7809 0.1451
-12.500 -0.6491 0.02415 0.01747 -0.1194 0.7732 0.1501
-12.250 -0.6375 0.02322 0.01650 -0.1187 0.7663 0.1553
-12.000 -0.6232 0.02249 0.01571 -0.1181 0.7607 0.1597
-11.750 -0.6138 0.02155 0.01478 -0.1170 0.7552 0.1647
-11.500 -0.6010 0.02084 0.01404 -0.1160 0.7496 0.1696
-11.250 -0.5874 0.02021 0.01336 -0.1150 0.7440 0.1737
-11.000 -0.5765 0.01950 0.01262 -0.1136 0.7388 0.1784
-10.750 -0.5634 0.01889 0.01201 -0.1124 0.7348 0.1833
-10.500 -0.5494 0.01836 0.01145 -0.1111 0.7306 0.1876
-10.250 -0.5385 0.01774 0.01084 -0.1094 0.7263 0.1927
-10.000 -0.5251 0.01725 0.01032 -0.1079 0.7222 0.1975
-9.750 -0.5097 0.01687 0.00988 -0.1066 0.7179 0.2015
-9.500 -0.4984 0.01636 0.00937 -0.1047 0.7143 0.2060
-9.250 -0.4851 0.01593 0.00895 -0.1029 0.7106 0.2107
-9.000 -0.4695 0.01559 0.00859 -0.1014 0.7072 0.2150
-8.750 -0.4568 0.01519 0.00820 -0.0994 0.7035 0.2197
-8.500 -0.4442 0.01483 0.00783 -0.0974 0.6997 0.2256
-8.250 -0.4287 0.01457 0.00753 -0.0956 0.6960 0.2317
-8.000 -0.4170 0.01423 0.00720 -0.0932 0.6923 0.2374
-7.750 -0.4024 0.01395 0.00694 -0.0913 0.6894 0.2431
-7.500 -0.3855 0.01373 0.00671 -0.0895 0.6858 0.2479
-7.250 -0.3716 0.01347 0.00646 -0.0873 0.6811 0.2520
-7.000 -0.3580 0.01324 0.00622 -0.0850 0.6762 0.2571
-6.750 -0.3420 0.01308 0.00600 -0.0829 0.6714 0.2617
-6.500 -0.3246 0.01291 0.00583 -0.0811 0.6678 0.2664
-6.250 -0.3108 0.01267 0.00563 -0.0787 0.6639 0.2718
-6.000 -0.2946 0.01250 0.00546 -0.0766 0.6600 0.2768
-5.750 -0.2769 0.01237 0.00531 -0.0748 0.6560 0.2820
-5.500 -0.2613 0.01221 0.00514 -0.0725 0.6522 0.2868
-5.250 -0.2461 0.01208 0.00499 -0.0702 0.6483 0.2918
-5.000 -0.2290 0.01196 0.00489 -0.0681 0.6449 0.2971
-4.750 -0.2104 0.01188 0.00480 -0.0663 0.6409 0.3015
-4.500 -0.1961 0.01177 0.00471 -0.0637 0.6366 0.3068
-4.250 -0.1813 0.01169 0.00463 -0.0611 0.6325 0.3121
-4.000 -0.1641 0.01165 0.00456 -0.0590 0.6285 0.3172
-3.750 -0.1441 0.01158 0.00449 -0.0574 0.6246 0.3221
-3.500 -0.1264 0.01147 0.00441 -0.0555 0.6200 0.3281
-3.250 -0.1069 0.01138 0.00434 -0.0538 0.6153 0.3341
-3.000 -0.0863 0.01134 0.00427 -0.0523 0.6106 0.3396
-2.750 -0.0671 0.01127 0.00419 -0.0506 0.6058 0.3454
-2.500 -0.0472 0.01117 0.00414 -0.0490 0.6009 0.3526
-2.250 -0.0261 0.01112 0.00408 -0.0476 0.5957 0.3591
-2.000 -0.0059 0.01106 0.00402 -0.0460 0.5902 0.3651
-1.750 0.0133 0.01099 0.00396 -0.0443 0.5850 0.3723
-1.500 0.0344 0.01093 0.00392 -0.0429 0.5789 0.3803
-1.250 0.0538 0.01087 0.00386 -0.0412 0.5724 0.3879
-1.000 0.0723 0.01082 0.00381 -0.0393 0.5663 0.3966
-0.500 0.1107 0.01069 0.00373 -0.0358 0.5520 0.4152
0.000 0.1456 0.01056 0.00368 -0.0316 0.5373 0.4417
0.250 0.1600 0.01052 0.00366 -0.0288 0.5288 0.4574
0.500 0.1755 0.01046 0.00367 -0.0263 0.5208 0.4770
0.750 0.1886 0.01045 0.00371 -0.0233 0.5116 0.4970
1.000 0.2006 0.01046 0.00374 -0.0201 0.5036 0.5134
1.250 0.2144 0.01051 0.00378 -0.0172 0.4943 0.5255
1.500 0.2265 0.01059 0.00384 -0.0140 0.4852 0.5358
1.750 0.2423 0.01069 0.00390 -0.0116 0.4763 0.5444
2.000 0.2541 0.01082 0.00402 -0.0085 0.4676 0.5512
2.250 0.2708 0.01094 0.00412 -0.0063 0.4591 0.5578
2.500 0.2848 0.01112 0.00425 -0.0036 0.4511 0.5634
2.750 0.3004 0.01126 0.00438 -0.0013 0.4434 0.5686
3.000 0.3157 0.01141 0.00453 0.0011 0.4360 0.5736
3.250 0.3286 0.01163 0.00471 0.0038 0.4286 0.5783
3.500 0.3466 0.01179 0.00485 0.0056 0.4222 0.5830
3.750 0.3618 0.01199 0.00502 0.0078 0.4156 0.5864
4.000 0.3750 0.01220 0.00522 0.0104 0.4096 0.5904
4.250 0.3927 0.01236 0.00539 0.0121 0.4037 0.5941
4.500 0.4083 0.01256 0.00560 0.0142 0.3978 0.5982
4.750 0.4217 0.01284 0.00584 0.0166 0.3917 0.6021
5.000 0.4387 0.01306 0.00605 0.0183 0.3869 0.6054
5.250 0.4561 0.01329 0.00627 0.0200 0.3816 0.6083
5.500 0.4697 0.01356 0.00655 0.0222 0.3756 0.6123
5.750 0.4830 0.01388 0.00686 0.0244 0.3706 0.6159
6.000 0.5009 0.01410 0.00711 0.0258 0.3659 0.6203
6.250 0.5166 0.01440 0.00742 0.0276 0.3608 0.6247
6.500 0.5308 0.01476 0.00776 0.0295 0.3556 0.6288
6.750 0.5448 0.01514 0.00814 0.0314 0.3508 0.6331
7.000 0.5619 0.01542 0.00847 0.0328 0.3459 0.6377
7.250 0.5775 0.01576 0.00884 0.0344 0.3412 0.6434
7.500 0.5908 0.01621 0.00929 0.0362 0.3363 0.6488
8.000 0.6226 0.01696 0.01012 0.0390 0.3276 0.6631
8.250 0.6373 0.01741 0.01060 0.0405 0.3223 0.6710
8.500 0.6512 0.01790 0.01112 0.0420 0.3178 0.6793
8.750 0.6658 0.01839 0.01165 0.0434 0.3136 0.6885
9.250 0.6982 0.01929 0.01269 0.0456 0.3045 0.7138
9.500 0.7111 0.01992 0.01337 0.0470 0.2997 0.7314
9.750 0.7274 0.02043 0.01397 0.0479 0.2957 0.7537
10.000 0.7466 0.02089 0.01455 0.0484 0.2910 0.7777
10.250 0.7657 0.02152 0.01528 0.0484 0.2860 0.8028
10.500 0.7903 0.02227 0.01613 0.0471 0.2811 0.8320
10.750 0.8452 0.02290 0.01697 0.0402 0.2755 0.8710
11.000 0.9285 0.02400 0.01819 0.0270 0.2676 0.9097
11.250 0.9991 0.02518 0.01942 0.0163 0.2594 0.9501
11.500 1.0277 0.02642 0.02065 0.0137 0.2514 0.9847
11.750 1.0453 0.02790 0.02209 0.0136 0.2448 0.9997
12.000 1.0576 0.02892 0.02310 0.0144 0.2382 1.0000
12.250 1.0636 0.03016 0.02431 0.0159 0.2333 1.0000
12.500 1.0755 0.03107 0.02523 0.0170 0.2295 1.0000
12.750 1.0863 0.03209 0.02625 0.0180 0.2248 1.0000
13.000 1.0937 0.03339 0.02754 0.0192 0.2201 1.0000
13.250 1.1028 0.03458 0.02873 0.0202 0.2165 1.0000
13.500 1.1144 0.03565 0.02982 0.0210 0.2127 1.0000
13.750 1.1237 0.03690 0.03109 0.0218 0.2084 1.0000
14.000 1.1308 0.03835 0.03252 0.0227 0.2042 1.0000
14.250 1.1397 0.03970 0.03389 0.0234 0.2005 1.0000
14.500 1.1493 0.04102 0.03523 0.0241 0.1961 1.0000
14.750 1.1556 0.04263 0.03685 0.0248 0.1915 1.0000
15.000 1.1612 0.04435 0.03856 0.0255 0.1872 1.0000
15.250 1.1705 0.04576 0.04000 0.0260 0.1830 1.0000
15.500 1.1750 0.04764 0.04189 0.0265 0.1784 1.0000
15.750 1.1793 0.04954 0.04380 0.0270 0.1745 1.0000
16.000 1.1866 0.05124 0.04553 0.0274 0.1703 1.0000
16.250 1.1897 0.05332 0.04761 0.0278 0.1653 1.0000
16.500 1.1914 0.05558 0.04989 0.0281 0.1610 1.0000
16.750 1.1962 0.05758 0.05191 0.0284 0.1564 1.0000
17.000 1.1959 0.06012 0.05446 0.0286 0.1515 1.0000
17.250 1.1974 0.06251 0.05688 0.0287 0.1468 1.0000
17.500 1.1976 0.06507 0.05946 0.0287 0.1420 1.0000
17.750 1.1952 0.06793 0.06233 0.0287 0.1377 1.0000
18.000 1.1955 0.07058 0.06501 0.0286 0.1332 1.0000
18.250 1.1929 0.07356 0.06801 0.0285 0.1287 1.0000
18.500 1.1902 0.07658 0.07106 0.0282 0.1248 1.0000
18.750 1.1874 0.07966 0.07417 0.0278 0.1203 1.0000
19.000 1.1809 0.08320 0.07772 0.0274 0.1159 1.0000
19.250 1.1792 0.08624 0.08081 0.0269 0.1125 1.0000
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