RAF 32 AIRFOIL (raf32-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 32 AIRFOIL (raf32-il) Reynolds number: 1,000,000 Max Cl/Cd: 152.3 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf32-il-1000000.txt Download as CSV file: xf-raf32-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 32 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6923 0.09299 0.09079 -0.0699 1.0000 0.0146
-15.500 -0.7401 0.08237 0.08005 -0.0749 1.0000 0.0144
-15.250 -0.7875 0.07306 0.07063 -0.0790 1.0000 0.0144
-15.000 -0.8357 0.06475 0.06221 -0.0820 1.0000 0.0142
-14.750 -0.8654 0.05470 0.05199 -0.0915 0.9983 0.0141
-14.500 -0.8878 0.04391 0.04100 -0.1041 0.9950 0.0141
-14.250 -0.8969 0.03427 0.03113 -0.1176 0.9900 0.0141
-14.000 -0.8862 0.02762 0.02422 -0.1310 0.9846 0.0144
-13.750 -0.8662 0.02544 0.02191 -0.1342 0.9810 0.0147
-13.500 -0.8452 0.02392 0.02029 -0.1359 0.9770 0.0150
-13.250 -0.8186 0.02261 0.01887 -0.1381 0.9748 0.0155
-13.000 -0.7901 0.02138 0.01753 -0.1404 0.9733 0.0159
-12.750 -0.7593 0.02031 0.01634 -0.1426 0.9722 0.0164
-12.500 -0.7263 0.01934 0.01525 -0.1451 0.9711 0.0167
-12.250 -0.7090 0.01797 0.01378 -0.1449 0.9643 0.0175
-12.000 -0.6791 0.01714 0.01289 -0.1464 0.9612 0.0182
-11.750 -0.6480 0.01640 0.01206 -0.1480 0.9587 0.0189
-11.500 -0.6217 0.01585 0.01144 -0.1483 0.9542 0.0196
-11.250 -0.5966 0.01537 0.01087 -0.1482 0.9487 0.0201
-11.000 -0.5701 0.01442 0.00983 -0.1490 0.9442 0.0212
-10.750 -0.5463 0.01391 0.00927 -0.1487 0.9382 0.0221
-10.500 -0.5208 0.01348 0.00877 -0.1486 0.9324 0.0230
-10.000 -0.4706 0.01255 0.00770 -0.1482 0.9204 0.0253
-9.750 -0.4437 0.01221 0.00732 -0.1483 0.9147 0.0267
-9.500 -0.4178 0.01195 0.00700 -0.1481 0.9089 0.0281
-9.250 -0.3930 0.01157 0.00656 -0.1477 0.9025 0.0296
-8.750 -0.3404 0.01111 0.00604 -0.1473 0.8909 0.0332
-8.500 -0.3142 0.01085 0.00570 -0.1471 0.8849 0.0349
-8.250 -0.2875 0.01067 0.00552 -0.1470 0.8795 0.0371
-8.000 -0.2608 0.01056 0.00539 -0.1467 0.8737 0.0390
-7.750 -0.2331 0.01050 0.00525 -0.1467 0.8685 0.0402
-7.500 -0.2081 0.01013 0.00486 -0.1463 0.8632 0.0426
-7.250 -0.1812 0.01004 0.00476 -0.1461 0.8576 0.0446
-7.000 -0.1538 0.00995 0.00462 -0.1460 0.8523 0.0463
-6.750 -0.1265 0.00989 0.00451 -0.1459 0.8472 0.0474
-6.500 -0.1017 0.00951 0.00409 -0.1454 0.8417 0.0498
-6.250 -0.0748 0.00935 0.00390 -0.1452 0.8367 0.0518
-6.000 -0.0479 0.00922 0.00375 -0.1451 0.8319 0.0535
-5.750 -0.0212 0.00910 0.00359 -0.1448 0.8266 0.0551
-5.500 0.0061 0.00903 0.00346 -0.1447 0.8214 0.0561
-5.250 0.0320 0.00874 0.00312 -0.1443 0.8163 0.0585
-5.000 0.0583 0.00853 0.00291 -0.1440 0.8110 0.0608
-4.750 0.0852 0.00841 0.00274 -0.1438 0.8059 0.0628
-4.500 0.1123 0.00830 0.00260 -0.1436 0.8008 0.0646
-4.250 0.1391 0.00820 0.00247 -0.1434 0.7952 0.0661
-4.000 0.1659 0.00805 0.00227 -0.1431 0.7896 0.0686
-3.750 0.1925 0.00790 0.00211 -0.1429 0.7843 0.0723
-3.500 0.2193 0.00778 0.00199 -0.1426 0.7782 0.0760
-3.250 0.2461 0.00770 0.00186 -0.1423 0.7722 0.0804
-3.000 0.2726 0.00754 0.00174 -0.1420 0.7656 0.0913
-2.750 0.2978 0.00728 0.00160 -0.1416 0.7581 0.1324
-2.500 0.3232 0.00702 0.00152 -0.1412 0.7508 0.1882
-2.250 0.3493 0.00689 0.00147 -0.1408 0.7434 0.2228
-2.000 0.3759 0.00683 0.00144 -0.1405 0.7369 0.2463
-1.750 0.4025 0.00677 0.00142 -0.1402 0.7296 0.2660
-1.500 0.4289 0.00674 0.00140 -0.1399 0.7228 0.2833
-1.250 0.4557 0.00670 0.00139 -0.1396 0.7155 0.2998
-0.750 0.5087 0.00665 0.00138 -0.1390 0.7016 0.3352
-0.500 0.5347 0.00663 0.00138 -0.1386 0.6944 0.3583
-0.250 0.5610 0.00656 0.00140 -0.1383 0.6879 0.3929
0.000 0.5869 0.00651 0.00143 -0.1379 0.6812 0.4301
0.250 0.6126 0.00646 0.00147 -0.1374 0.6751 0.4748
0.500 0.6386 0.00641 0.00153 -0.1371 0.6687 0.5178
0.750 0.6639 0.00640 0.00159 -0.1365 0.6625 0.5631
1.000 0.6902 0.00637 0.00165 -0.1362 0.6571 0.5965
1.250 0.7162 0.00637 0.00171 -0.1357 0.6513 0.6233
1.500 0.7412 0.00640 0.00178 -0.1351 0.6446 0.6523
1.750 0.7666 0.00638 0.00184 -0.1346 0.6376 0.6845
2.000 0.7906 0.00640 0.00192 -0.1337 0.6307 0.7236
2.250 0.8150 0.00633 0.00200 -0.1329 0.6246 0.7722
2.500 0.8359 0.00619 0.00209 -0.1313 0.6179 0.8541
2.750 0.8931 0.00616 0.00222 -0.1379 0.6095 1.0000
3.000 0.9163 0.00629 0.00229 -0.1369 0.5990 1.0000
3.250 0.9409 0.00637 0.00237 -0.1362 0.5895 1.0000
3.500 0.9645 0.00650 0.00245 -0.1353 0.5815 1.0000
3.750 0.9897 0.00658 0.00253 -0.1347 0.5740 1.0000
4.000 1.0129 0.00671 0.00263 -0.1337 0.5641 1.0000
4.250 1.0365 0.00683 0.00273 -0.1328 0.5535 1.0000
4.500 1.0600 0.00696 0.00284 -0.1319 0.5427 1.0000
4.750 1.0822 0.00712 0.00296 -0.1308 0.5299 1.0000
5.000 1.1031 0.00731 0.00309 -0.1294 0.5129 1.0000
5.250 1.1228 0.00753 0.00325 -0.1277 0.4933 1.0000
5.500 1.1396 0.00784 0.00345 -0.1255 0.4683 1.0000
5.750 1.1522 0.00823 0.00369 -0.1225 0.4379 1.0000
6.000 1.1657 0.00863 0.00396 -0.1196 0.4111 1.0000
6.250 1.1796 0.00904 0.00424 -0.1170 0.3826 1.0000
6.500 1.1923 0.00952 0.00457 -0.1141 0.3506 1.0000
6.750 1.2019 0.01014 0.00499 -0.1108 0.3088 1.0000
7.000 1.2074 0.01095 0.00554 -0.1068 0.2598 1.0000
7.250 1.2160 0.01167 0.00606 -0.1035 0.2258 1.0000
7.500 1.2263 0.01234 0.00658 -0.1005 0.1969 1.0000
7.750 1.2367 0.01302 0.00712 -0.0976 0.1682 1.0000
8.000 1.2439 0.01387 0.00778 -0.0943 0.1325 1.0000
8.250 1.2473 0.01494 0.00862 -0.0906 0.0936 1.0000
8.500 1.2563 0.01578 0.00935 -0.0878 0.0750 1.0000
8.750 1.2694 0.01644 0.00997 -0.0857 0.0665 1.0000
9.000 1.2841 0.01704 0.01056 -0.0839 0.0607 1.0000
9.250 1.2981 0.01768 0.01120 -0.0820 0.0562 1.0000
9.500 1.3127 0.01832 0.01184 -0.0803 0.0517 1.0000
9.750 1.3273 0.01897 0.01250 -0.0786 0.0479 1.0000
10.000 1.3403 0.01973 0.01324 -0.0768 0.0434 1.0000
10.250 1.3543 0.02045 0.01396 -0.0752 0.0393 1.0000
10.500 1.3669 0.02128 0.01479 -0.0735 0.0354 1.0000
10.750 1.3796 0.02212 0.01563 -0.0718 0.0325 1.0000
11.000 1.3909 0.02307 0.01659 -0.0700 0.0297 1.0000
11.250 1.4034 0.02397 0.01751 -0.0685 0.0277 1.0000
11.500 1.4129 0.02509 0.01865 -0.0667 0.0256 1.0000
11.750 1.4242 0.02611 0.01971 -0.0651 0.0243 1.0000
12.000 1.4356 0.02715 0.02079 -0.0637 0.0231 1.0000
12.250 1.4453 0.02834 0.02200 -0.0621 0.0220 1.0000
12.500 1.4509 0.02988 0.02358 -0.0603 0.0208 1.0000
12.750 1.4618 0.03104 0.02480 -0.0590 0.0201 1.0000
13.000 1.4717 0.03230 0.02611 -0.0577 0.0195 1.0000
13.250 1.4810 0.03365 0.02751 -0.0564 0.0188 1.0000
13.500 1.4889 0.03513 0.02902 -0.0551 0.0180 1.0000
13.750 1.4925 0.03703 0.03097 -0.0536 0.0173 1.0000
14.000 1.4961 0.03898 0.03300 -0.0522 0.0167 1.0000
14.250 1.5050 0.04050 0.03458 -0.0512 0.0164 1.0000
14.500 1.5124 0.04219 0.03633 -0.0503 0.0159 1.0000
14.750 1.5187 0.04401 0.03821 -0.0493 0.0154 1.0000
15.000 1.5245 0.04592 0.04018 -0.0484 0.0150 1.0000
15.250 1.5286 0.04804 0.04235 -0.0476 0.0146 1.0000
15.500 1.5306 0.05042 0.04480 -0.0467 0.0143 1.0000
15.750 1.5270 0.05347 0.04793 -0.0459 0.0139 1.0000
16.000 1.5254 0.05636 0.05090 -0.0452 0.0136 1.0000
16.250 1.5302 0.05860 0.05323 -0.0447 0.0134 1.0000
16.500 1.5351 0.06086 0.05556 -0.0444 0.0130 1.0000
16.750 1.5365 0.06356 0.05835 -0.0441 0.0128 1.0000
17.000 1.5392 0.06617 0.06102 -0.0439 0.0125 1.0000
17.250 1.5402 0.06901 0.06394 -0.0438 0.0122 1.0000
17.500 1.5406 0.07198 0.06698 -0.0438 0.0120 1.0000
17.750 1.5401 0.07512 0.07019 -0.0439 0.0118 1.0000
18.000 1.5374 0.07862 0.07377 -0.0442 0.0116 1.0000
18.250 1.5319 0.08258 0.07780 -0.0446 0.0114 1.0000
18.500 1.5238 0.08696 0.08228 -0.0453 0.0112 1.0000
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