RAF 32 AIRFOIL (raf32-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 32 AIRFOIL (raf32-il) Reynolds number: 500,000 Max Cl/Cd: 123.68 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf32-il-500000.txt Download as CSV file: xf-raf32-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.2063 0.13069 0.12842 -0.0615 0.9907 0.0306
-13.250 -0.1988 0.12729 0.12500 -0.0639 0.9893 0.0324
-12.750 -0.7529 0.04104 0.03780 -0.1083 0.9881 0.0212
-12.500 -0.7381 0.03527 0.03183 -0.1209 0.9833 0.0217
-12.250 -0.7240 0.03265 0.02904 -0.1247 0.9757 0.0222
-12.000 -0.6998 0.02990 0.02604 -0.1294 0.9725 0.0229
-11.750 -0.6806 0.02777 0.02366 -0.1315 0.9672 0.0236
-11.500 -0.6566 0.02599 0.02160 -0.1335 0.9626 0.0241
-11.250 -0.6305 0.02375 0.01922 -0.1361 0.9601 0.0252
-11.000 -0.5971 0.02283 0.01824 -0.1386 0.9588 0.0261
-10.750 -0.5631 0.02185 0.01714 -0.1411 0.9578 0.0272
-10.500 -0.5432 0.02104 0.01616 -0.1404 0.9514 0.0283
-10.250 -0.5155 0.01978 0.01477 -0.1417 0.9482 0.0295
-10.000 -0.4830 0.01919 0.01416 -0.1433 0.9461 0.0308
-9.750 -0.4494 0.01860 0.01348 -0.1451 0.9442 0.0323
-9.500 -0.4227 0.01802 0.01274 -0.1453 0.9401 0.0337
-9.250 -0.3998 0.01716 0.01182 -0.1450 0.9345 0.0353
-9.000 -0.3681 0.01691 0.01157 -0.1461 0.9314 0.0370
-8.750 -0.3359 0.01652 0.01107 -0.1473 0.9286 0.0391
-8.500 -0.3133 0.01598 0.01040 -0.1465 0.9225 0.0408
-8.250 -0.2868 0.01545 0.00987 -0.1466 0.9177 0.0427
-8.000 -0.2563 0.01521 0.00958 -0.1474 0.9142 0.0450
-7.750 -0.2294 0.01503 0.00929 -0.1472 0.9092 0.0471
-7.500 -0.2060 0.01426 0.00845 -0.1467 0.9033 0.0494
-7.250 -0.1772 0.01393 0.00811 -0.1471 0.8990 0.0516
-7.000 -0.1504 0.01372 0.00783 -0.1470 0.8940 0.0542
-6.750 -0.1242 0.01356 0.00758 -0.1466 0.8884 0.0560
-6.500 -0.0985 0.01275 0.00672 -0.1465 0.8837 0.0588
-6.250 -0.0721 0.01247 0.00641 -0.1464 0.8786 0.0613
-6.000 -0.0464 0.01222 0.00612 -0.1460 0.8726 0.0637
-5.750 -0.0180 0.01200 0.00581 -0.1461 0.8679 0.0658
-5.500 0.0072 0.01157 0.00532 -0.1456 0.8625 0.0681
-5.250 0.0320 0.01116 0.00491 -0.1451 0.8567 0.0710
-5.000 0.0600 0.01092 0.00462 -0.1452 0.8519 0.0737
-4.750 0.0860 0.01073 0.00437 -0.1448 0.8463 0.0763
-4.500 0.1124 0.01057 0.00415 -0.1445 0.8403 0.0782
-4.250 0.1398 0.01019 0.00373 -0.1444 0.8353 0.0823
-4.000 0.1650 0.00998 0.00352 -0.1439 0.8294 0.0864
-3.750 0.1917 0.00983 0.00332 -0.1436 0.8235 0.0906
-3.500 0.2198 0.00958 0.00307 -0.1436 0.8184 0.0991
-3.250 0.2443 0.00934 0.00289 -0.1430 0.8118 0.1154
-3.000 0.2698 0.00893 0.00272 -0.1427 0.8060 0.1820
-2.750 0.2964 0.00873 0.00266 -0.1425 0.8002 0.2340
-2.500 0.3223 0.00863 0.00261 -0.1420 0.7935 0.2623
-2.250 0.3503 0.00856 0.00254 -0.1420 0.7877 0.2849
-2.000 0.3757 0.00849 0.00251 -0.1415 0.7803 0.3040
-1.750 0.4027 0.00842 0.00244 -0.1412 0.7735 0.3231
-1.500 0.4290 0.00837 0.00241 -0.1408 0.7667 0.3434
-1.250 0.4551 0.00828 0.00238 -0.1405 0.7598 0.3658
-1.000 0.4823 0.00823 0.00235 -0.1403 0.7540 0.3922
-0.750 0.5075 0.00813 0.00236 -0.1397 0.7469 0.4275
-0.500 0.5340 0.00804 0.00237 -0.1394 0.7409 0.4737
-0.250 0.5591 0.00795 0.00243 -0.1388 0.7343 0.5230
0.000 0.5847 0.00789 0.00247 -0.1383 0.7279 0.5700
0.250 0.6109 0.00786 0.00251 -0.1379 0.7221 0.6112
0.750 0.6618 0.00778 0.00259 -0.1367 0.7095 0.6806
1.000 0.6863 0.00773 0.00267 -0.1359 0.7033 0.7191
1.250 0.7104 0.00767 0.00272 -0.1350 0.6971 0.7654
1.500 0.7341 0.00754 0.00277 -0.1340 0.6916 0.8335
1.750 0.7942 0.00740 0.00286 -0.1409 0.6853 1.0000
2.000 0.8201 0.00751 0.00290 -0.1405 0.6794 1.0000
2.250 0.8451 0.00761 0.00297 -0.1399 0.6725 1.0000
2.500 0.8697 0.00771 0.00303 -0.1392 0.6648 1.0000
2.750 0.8947 0.00782 0.00310 -0.1386 0.6575 1.0000
3.000 0.9192 0.00792 0.00318 -0.1378 0.6500 1.0000
3.250 0.9439 0.00805 0.00328 -0.1372 0.6423 1.0000
3.500 0.9676 0.00816 0.00336 -0.1362 0.6332 1.0000
3.750 0.9904 0.00827 0.00346 -0.1351 0.6227 1.0000
4.000 1.0139 0.00843 0.00355 -0.1342 0.6132 1.0000
4.250 1.0369 0.00853 0.00368 -0.1332 0.6039 1.0000
4.500 1.0603 0.00868 0.00381 -0.1323 0.5953 1.0000
4.750 1.0830 0.00881 0.00394 -0.1312 0.5856 1.0000
5.000 1.1054 0.00895 0.00409 -0.1301 0.5755 1.0000
5.250 1.1267 0.00911 0.00423 -0.1287 0.5641 1.0000
5.500 1.1469 0.00928 0.00437 -0.1271 0.5511 1.0000
5.750 1.1665 0.00945 0.00455 -0.1255 0.5368 1.0000
6.000 1.1834 0.00968 0.00472 -0.1232 0.5177 1.0000
6.250 1.1970 0.00995 0.00492 -0.1203 0.4935 1.0000
6.500 1.2077 0.01030 0.00517 -0.1169 0.4692 1.0000
6.750 1.2176 0.01073 0.00549 -0.1134 0.4432 1.0000
7.000 1.2287 0.01120 0.00585 -0.1103 0.4168 1.0000
7.250 1.2386 0.01174 0.00627 -0.1070 0.3886 1.0000
7.500 1.2461 0.01240 0.00678 -0.1034 0.3531 1.0000
7.750 1.2508 0.01323 0.00739 -0.0995 0.3103 1.0000
8.000 1.2516 0.01431 0.00820 -0.0952 0.2618 1.0000
8.250 1.2549 0.01537 0.00904 -0.0914 0.2249 1.0000
8.500 1.2602 0.01638 0.00988 -0.0881 0.1925 1.0000
8.750 1.2630 0.01759 0.01086 -0.0845 0.1525 1.0000
9.000 1.2625 0.01903 0.01203 -0.0808 0.1083 1.0000
9.250 1.2659 0.02033 0.01318 -0.0777 0.0848 1.0000
9.500 1.2732 0.02146 0.01425 -0.0752 0.0737 1.0000
9.750 1.2838 0.02241 0.01522 -0.0732 0.0673 1.0000
10.000 1.2927 0.02351 0.01632 -0.0710 0.0613 1.0000
10.250 1.3029 0.02455 0.01737 -0.0691 0.0563 1.0000
10.500 1.3105 0.02581 0.01865 -0.0671 0.0516 1.0000
10.750 1.3217 0.02684 0.01973 -0.0654 0.0478 1.0000
11.000 1.3262 0.02838 0.02126 -0.0633 0.0439 1.0000
11.250 1.3390 0.02936 0.02230 -0.0619 0.0410 1.0000
11.500 1.3474 0.03068 0.02363 -0.0603 0.0382 1.0000
11.750 1.3526 0.03229 0.02528 -0.0585 0.0359 1.0000
12.000 1.3624 0.03359 0.02664 -0.0572 0.0339 1.0000
12.250 1.3701 0.03509 0.02818 -0.0558 0.0323 1.0000
12.500 1.3720 0.03712 0.03024 -0.0541 0.0307 1.0000
12.750 1.3794 0.03873 0.03193 -0.0528 0.0294 1.0000
13.000 1.3868 0.04038 0.03365 -0.0517 0.0281 1.0000
13.250 1.3926 0.04222 0.03555 -0.0505 0.0271 1.0000
13.500 1.3966 0.04428 0.03765 -0.0494 0.0262 1.0000
13.750 1.3922 0.04720 0.04062 -0.0480 0.0251 1.0000
14.000 1.3989 0.04912 0.04264 -0.0472 0.0246 1.0000
14.250 1.4041 0.05123 0.04484 -0.0464 0.0239 1.0000
14.500 1.4086 0.05344 0.04713 -0.0457 0.0231 1.0000
14.750 1.4126 0.05575 0.04950 -0.0451 0.0225 1.0000
15.000 1.4157 0.05819 0.05200 -0.0446 0.0219 1.0000
15.250 1.4153 0.06106 0.05492 -0.0440 0.0212 1.0000
15.500 1.4122 0.06424 0.05816 -0.0434 0.0206 1.0000
15.750 1.4172 0.06663 0.06066 -0.0432 0.0202 1.0000
16.000 1.4205 0.06926 0.06340 -0.0430 0.0197 1.0000
16.250 1.4232 0.07200 0.06624 -0.0429 0.0193 1.0000
16.500 1.4257 0.07480 0.06913 -0.0429 0.0188 1.0000
16.750 1.4275 0.07775 0.07215 -0.0430 0.0184 1.0000
17.000 1.4287 0.08076 0.07524 -0.0432 0.0181 1.0000
17.250 1.4295 0.08388 0.07842 -0.0435 0.0177 1.0000
17.500 1.4295 0.08710 0.08170 -0.0438 0.0174 1.0000
17.750 1.4286 0.09023 0.08489 -0.0436 0.0169 1.0000
18.000 1.4283 0.09375 0.08855 -0.0443 0.0167 1.0000
18.250 1.4276 0.09735 0.09228 -0.0452 0.0164 1.0000
18.500 1.4266 0.10103 0.09610 -0.0462 0.0162 1.0000
18.750 1.4252 0.10482 0.10001 -0.0472 0.0159 1.0000
19.000 1.4231 0.10878 0.10409 -0.0486 0.0156 1.0000
19.250 1.4207 0.11284 0.10826 -0.0501 0.0153 1.0000
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Polar data table (+)
Polar graphs
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