RAF 32 MOD AIRFOIL (raf32md-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 32 MOD AIRFOIL (raf32md-il) Reynolds number: 500,000 Max Cl/Cd: 120.81 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf32md-il-500000.txt Download as CSV file: xf-raf32md-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 32 MOD 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3758 0.08363 0.08145 -0.0542 0.9945 0.0283
-8.750 -0.4219 0.05022 0.04792 -0.0896 0.9818 0.0217
-8.500 -0.4215 0.03712 0.03422 -0.1060 0.9723 0.0211
-8.250 -0.4098 0.03056 0.02699 -0.1105 0.9650 0.0214
-8.000 -0.3880 0.02581 0.02158 -0.1137 0.9609 0.0225
-7.750 -0.3560 0.02441 0.02018 -0.1161 0.9594 0.0237
-7.500 -0.3219 0.02331 0.01897 -0.1184 0.9582 0.0251
-7.250 -0.2936 0.02145 0.01681 -0.1196 0.9549 0.0262
-7.000 -0.2687 0.01996 0.01504 -0.1196 0.9494 0.0271
-6.750 -0.2355 0.01983 0.01470 -0.1207 0.9466 0.0283
-6.500 -0.2081 0.01654 0.01113 -0.1221 0.9439 0.0303
-6.250 -0.1820 0.01564 0.01014 -0.1220 0.9389 0.0315
-6.000 -0.1546 0.01482 0.00923 -0.1221 0.9339 0.0326
-5.750 -0.1240 0.01408 0.00838 -0.1228 0.9303 0.0341
-5.500 -0.0956 0.01353 0.00772 -0.1229 0.9257 0.0355
-5.250 -0.0694 0.01303 0.00713 -0.1225 0.9196 0.0363
-5.000 -0.0410 0.01217 0.00616 -0.1227 0.9152 0.0372
-4.750 -0.0167 0.01128 0.00521 -0.1222 0.9090 0.0391
-4.500 0.0100 0.01079 0.00467 -0.1219 0.9031 0.0406
-4.250 0.0388 0.01038 0.00420 -0.1221 0.8985 0.0420
-4.000 0.0638 0.01006 0.00383 -0.1215 0.8914 0.0434
-3.750 0.0920 0.00976 0.00346 -0.1215 0.8860 0.0450
-3.500 0.1187 0.00955 0.00319 -0.1212 0.8796 0.0467
-3.250 0.1457 0.00924 0.00283 -0.1209 0.8733 0.0505
-3.000 0.1735 0.00902 0.00258 -0.1208 0.8676 0.0564
-2.750 0.1991 0.00865 0.00240 -0.1204 0.8606 0.1036
-2.500 0.2268 0.00830 0.00222 -0.1205 0.8551 0.1638
-2.250 0.2514 0.00795 0.00217 -0.1200 0.8476 0.2494
-2.000 0.2790 0.00779 0.00210 -0.1200 0.8416 0.3012
-1.750 0.3053 0.00769 0.00206 -0.1196 0.8344 0.3338
-1.500 0.3326 0.00759 0.00200 -0.1195 0.8278 0.3658
-1.250 0.3590 0.00745 0.00196 -0.1192 0.8208 0.4034
-1.000 0.3853 0.00728 0.00192 -0.1188 0.8137 0.4519
-0.750 0.4107 0.00709 0.00199 -0.1184 0.8066 0.5426
-0.500 0.4369 0.00701 0.00200 -0.1179 0.7991 0.5986
-0.250 0.4627 0.00693 0.00202 -0.1174 0.7917 0.6424
0.000 0.4879 0.00681 0.00203 -0.1167 0.7840 0.6901
0.250 0.5126 0.00669 0.00207 -0.1158 0.7761 0.7427
0.500 0.5365 0.00653 0.00208 -0.1148 0.7683 0.8072
0.750 0.5926 0.00622 0.00207 -0.1207 0.7609 0.9985
1.000 0.6195 0.00629 0.00207 -0.1205 0.7527 1.0000
1.250 0.6448 0.00635 0.00210 -0.1199 0.7434 1.0000
1.500 0.6709 0.00643 0.00212 -0.1194 0.7348 1.0000
1.750 0.6964 0.00651 0.00217 -0.1189 0.7252 1.0000
2.000 0.7221 0.00659 0.00222 -0.1184 0.7156 1.0000
2.250 0.7477 0.00669 0.00226 -0.1178 0.7053 1.0000
2.500 0.7728 0.00679 0.00231 -0.1172 0.6933 1.0000
2.750 0.7976 0.00689 0.00239 -0.1164 0.6802 1.0000
3.000 0.8217 0.00701 0.00245 -0.1156 0.6643 1.0000
3.250 0.8456 0.00715 0.00253 -0.1147 0.6476 1.0000
3.500 0.8695 0.00729 0.00263 -0.1138 0.6307 1.0000
3.750 0.8939 0.00745 0.00275 -0.1130 0.6163 1.0000
4.000 0.9178 0.00761 0.00288 -0.1122 0.6003 1.0000
4.250 0.9411 0.00779 0.00302 -0.1112 0.5811 1.0000
4.500 0.9638 0.00801 0.00318 -0.1101 0.5613 1.0000
4.750 0.9868 0.00821 0.00335 -0.1091 0.5410 1.0000
5.000 1.0085 0.00847 0.00354 -0.1079 0.5169 1.0000
5.250 1.0281 0.00882 0.00377 -0.1062 0.4807 1.0000
5.500 1.0447 0.00933 0.00406 -0.1041 0.4305 1.0000
5.750 1.0584 0.01004 0.00446 -0.1015 0.3657 1.0000
6.000 1.0689 0.01101 0.00499 -0.0985 0.2850 1.0000
6.250 1.0777 0.01214 0.00566 -0.0953 0.2009 1.0000
6.500 1.0891 0.01310 0.00629 -0.0926 0.1424 1.0000
6.750 1.1004 0.01405 0.00694 -0.0898 0.0907 1.0000
7.000 1.1144 0.01474 0.00750 -0.0875 0.0698 1.0000
7.250 1.1289 0.01533 0.00805 -0.0851 0.0592 1.0000
7.500 1.1447 0.01584 0.00856 -0.0831 0.0519 1.0000
7.750 1.1599 0.01640 0.00914 -0.0809 0.0443 1.0000
8.000 1.1727 0.01711 0.00983 -0.0784 0.0368 1.0000
8.250 1.1869 0.01775 0.01044 -0.0762 0.0312 1.0000
8.500 1.1999 0.01846 0.01120 -0.0738 0.0276 1.0000
8.750 1.2138 0.01913 0.01190 -0.0716 0.0251 1.0000
9.000 1.2198 0.02030 0.01310 -0.0684 0.0229 1.0000
9.250 1.2336 0.02100 0.01388 -0.0664 0.0219 1.0000
9.500 1.2460 0.02181 0.01477 -0.0642 0.0207 1.0000
9.750 1.2589 0.02260 0.01558 -0.0623 0.0192 1.0000
10.000 1.2657 0.02384 0.01687 -0.0597 0.0183 1.0000
10.250 1.2687 0.02544 0.01856 -0.0567 0.0174 1.0000
10.500 1.2800 0.02647 0.01967 -0.0548 0.0169 1.0000
10.750 1.2893 0.02771 0.02100 -0.0527 0.0165 1.0000
11.000 1.2992 0.02891 0.02231 -0.0509 0.0158 1.0000
11.250 1.3082 0.03025 0.02372 -0.0491 0.0153 1.0000
11.500 1.3171 0.03162 0.02516 -0.0474 0.0148 1.0000
11.750 1.3250 0.03315 0.02675 -0.0456 0.0144 1.0000
12.000 1.3310 0.03498 0.02865 -0.0439 0.0139 1.0000
12.250 1.3359 0.03761 0.03141 -0.0419 0.0133 1.0000
12.500 1.3444 0.03906 0.03300 -0.0406 0.0131 1.0000
12.750 1.3520 0.04068 0.03476 -0.0392 0.0127 1.0000
13.000 1.3585 0.04264 0.03687 -0.0379 0.0124 1.0000
13.250 1.3636 0.04476 0.03914 -0.0366 0.0121 1.0000
13.500 1.3677 0.04696 0.04148 -0.0354 0.0118 1.0000
13.750 1.3702 0.04940 0.04407 -0.0343 0.0116 1.0000
14.000 1.3714 0.05197 0.04678 -0.0333 0.0114 1.0000
14.250 1.3703 0.05495 0.04994 -0.0325 0.0113 1.0000
14.500 1.3684 0.05793 0.05306 -0.0319 0.0110 1.0000
14.750 1.3650 0.06121 0.05649 -0.0316 0.0109 1.0000
15.000 1.3599 0.06484 0.06027 -0.0315 0.0108 1.0000
15.250 1.3530 0.06886 0.06445 -0.0317 0.0107 1.0000
15.500 1.3439 0.07338 0.06914 -0.0323 0.0106 1.0000
15.750 1.3333 0.07826 0.07420 -0.0334 0.0105 1.0000
16.000 1.3206 0.08372 0.07984 -0.0349 0.0105 1.0000
16.250 1.3052 0.08992 0.08624 -0.0371 0.0105 1.0000
16.500 1.2889 0.09653 0.09304 -0.0399 0.0104 1.0000
16.750 1.2696 0.10413 0.10086 -0.0435 0.0105 1.0000
17.000 1.2497 0.11227 0.10919 -0.0479 0.0105 1.0000
17.250 1.2223 0.12275 0.11993 -0.0541 0.0106 1.0000
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