RAF 32 AIRFOIL (raf32-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 32 AIRFOIL (raf32-il) Reynolds number: 100,000 Max Cl/Cd: 56.15 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf32-il-100000.txt Download as CSV file: xf-raf32-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4037 0.11342 0.10892 -0.0281 1.0000 0.1320
-8.500 -0.4400 0.11299 0.10862 -0.0282 1.0000 0.1338
-8.250 -0.4760 0.11241 0.10817 -0.0274 1.0000 0.1343
-8.000 -0.4271 0.10715 0.10282 -0.0232 1.0000 0.1396
-7.750 -0.4243 0.10459 0.10027 -0.0248 0.9973 0.1451
-7.500 -0.4627 0.10095 0.09675 -0.0385 0.9855 0.1500
-7.250 -0.4080 0.09724 0.09293 -0.0322 0.9858 0.1555
-6.750 -0.3968 0.09038 0.08608 -0.0399 0.9718 0.1695
-6.250 -0.4205 0.05366 0.04829 -0.0809 0.9515 0.1072
-6.000 -0.3955 0.04618 0.03997 -0.0866 0.9463 0.1036
-5.750 -0.3604 0.04129 0.03417 -0.0914 0.9427 0.1057
-5.500 -0.3436 0.03898 0.03176 -0.0910 0.9358 0.1081
-5.250 -0.3124 0.03767 0.03030 -0.0926 0.9311 0.1135
-5.000 -0.2725 0.03546 0.02740 -0.0957 0.9277 0.1178
-4.750 -0.2554 0.03405 0.02568 -0.0946 0.9201 0.1215
-4.500 -0.2215 0.03303 0.02456 -0.0963 0.9155 0.1267
-4.250 -0.1847 0.03224 0.02339 -0.0982 0.9117 0.1332
-4.000 -0.1669 0.03140 0.02247 -0.0969 0.9043 0.1373
-3.750 -0.1319 0.03079 0.02178 -0.0984 0.8998 0.1441
-3.500 -0.0988 0.03022 0.02106 -0.0996 0.8954 0.1518
-3.250 -0.0797 0.02991 0.02078 -0.0984 0.8883 0.1582
-3.000 -0.0437 0.02943 0.02029 -0.1000 0.8840 0.1699
-2.750 -0.0172 0.02919 0.02009 -0.1000 0.8784 0.1841
-2.500 0.0056 0.02897 0.01998 -0.0994 0.8719 0.2034
-2.250 0.0421 0.02853 0.01981 -0.1010 0.8679 0.2619
-2.000 0.0608 0.02855 0.02006 -0.0998 0.8611 0.3274
-1.750 0.0870 0.02858 0.02022 -0.0998 0.8551 0.3782
-1.500 0.1260 0.02850 0.02026 -0.1017 0.8514 0.4267
-1.250 0.1375 0.02887 0.02074 -0.0993 0.8430 0.4563
-1.000 0.1694 0.02888 0.02086 -0.0999 0.8379 0.4988
-0.750 0.2084 0.02878 0.02095 -0.1014 0.8348 0.5567
-0.500 0.2119 0.02928 0.02159 -0.0976 0.8248 0.5971
-0.250 0.2468 0.02908 0.02162 -0.0982 0.8208 0.6669
0.000 0.2633 0.02922 0.02201 -0.0962 0.8136 0.7358
0.250 0.3134 0.02869 0.02193 -0.1004 0.8085 1.0000
0.500 0.3575 0.02878 0.02173 -0.1036 0.8048 1.0000
0.750 0.3714 0.02956 0.02237 -0.1021 0.7959 1.0000
1.000 0.4053 0.02978 0.02244 -0.1033 0.7907 1.0000
1.250 0.4501 0.02970 0.02223 -0.1059 0.7878 1.0000
1.500 0.4539 0.03077 0.02322 -0.1029 0.7767 1.0000
1.750 0.4942 0.03076 0.02312 -0.1048 0.7732 1.0000
2.000 0.5041 0.03173 0.02403 -0.1026 0.7633 1.0000
2.250 0.5400 0.03179 0.02403 -0.1038 0.7586 1.0000
2.500 0.5847 0.03155 0.02374 -0.1061 0.7560 1.0000
2.750 0.5860 0.03287 0.02504 -0.1029 0.7441 1.0000
3.000 0.6295 0.03257 0.02471 -0.1049 0.7411 1.0000
3.250 0.6327 0.03393 0.02606 -0.1020 0.7296 1.0000
3.500 0.6743 0.03363 0.02577 -0.1036 0.7262 1.0000
3.750 0.7184 0.03319 0.02533 -0.1055 0.7236 1.0000
4.000 0.7203 0.03464 0.02680 -0.1025 0.7112 1.0000
4.250 0.7669 0.03395 0.02615 -0.1045 0.7091 1.0000
4.500 0.7674 0.03555 0.02776 -0.1014 0.6962 1.0000
4.750 0.7846 0.03632 0.02857 -0.1001 0.6873 1.0000
5.000 0.8249 0.03552 0.02783 -0.1009 0.6812 1.0000
5.250 0.8895 0.03300 0.02538 -0.1039 0.6794 1.0000
5.500 0.9586 0.03063 0.02313 -0.1082 0.6780 1.0000
5.750 0.9585 0.03189 0.02444 -0.1042 0.6651 1.0000
6.000 1.0228 0.03004 0.02273 -0.1084 0.6630 1.0000
6.250 1.0253 0.03111 0.02386 -0.1046 0.6508 1.0000
6.500 1.1030 0.02854 0.02146 -0.1105 0.6476 1.0000
6.750 1.1284 0.02810 0.02111 -0.1092 0.6353 1.0000
7.000 1.1774 0.02636 0.01945 -0.1107 0.6225 1.0000
7.250 1.2185 0.02514 0.01831 -0.1114 0.6082 1.0000
7.500 1.2486 0.02435 0.01757 -0.1105 0.5912 1.0000
7.750 1.2720 0.02384 0.01711 -0.1087 0.5728 1.0000
8.000 1.2929 0.02350 0.01683 -0.1066 0.5540 1.0000
8.250 1.3084 0.02330 0.01667 -0.1036 0.5336 1.0000
8.500 1.3090 0.02353 0.01696 -0.0984 0.5118 1.0000
8.750 1.3159 0.02364 0.01703 -0.0943 0.4860 1.0000
9.000 1.3186 0.02402 0.01735 -0.0897 0.4563 1.0000
9.250 1.3166 0.02476 0.01802 -0.0848 0.4223 1.0000
9.500 1.3109 0.02584 0.01892 -0.0797 0.3807 1.0000
9.750 1.2995 0.02744 0.02027 -0.0744 0.3293 1.0000
10.000 1.2823 0.02972 0.02212 -0.0690 0.2728 1.0000
10.250 1.2628 0.03260 0.02455 -0.0642 0.2216 1.0000
10.500 1.2470 0.03563 0.02718 -0.0602 0.1820 1.0000
10.750 1.2383 0.03838 0.02966 -0.0571 0.1541 1.0000
11.000 1.2355 0.04081 0.03189 -0.0547 0.1363 1.0000
11.250 1.2367 0.04303 0.03398 -0.0526 0.1227 1.0000
11.500 1.2418 0.04504 0.03586 -0.0508 0.1119 1.0000
11.750 1.2517 0.04678 0.03763 -0.0492 0.1024 1.0000
12.000 1.2678 0.04837 0.03913 -0.0479 0.0942 1.0000
12.250 1.2982 0.04965 0.04013 -0.0474 0.0857 1.0000
12.500 1.3126 0.05137 0.04210 -0.0462 0.0810 1.0000
12.750 1.3645 0.05299 0.04348 -0.0475 0.0736 1.0000
13.000 1.3718 0.05505 0.04588 -0.0459 0.0711 1.0000
13.250 1.3892 0.05723 0.04827 -0.0450 0.0679 1.0000
13.500 1.4102 0.05961 0.05077 -0.0446 0.0653 1.0000
13.750 1.4426 0.06339 0.05465 -0.0453 0.0622 1.0000
14.000 1.4340 0.06619 0.05780 -0.0429 0.0614 1.0000
14.250 1.4243 0.06934 0.06130 -0.0408 0.0605 1.0000
14.500 1.4146 0.07293 0.06523 -0.0390 0.0598 1.0000
14.750 1.4026 0.07690 0.06952 -0.0375 0.0594 1.0000
15.000 1.3874 0.08126 0.07419 -0.0364 0.0593 1.0000
15.250 1.3693 0.08598 0.07922 -0.0357 0.0592 1.0000
15.500 1.3486 0.09115 0.08468 -0.0356 0.0593 1.0000
15.750 1.3252 0.09678 0.09059 -0.0361 0.0595 1.0000
16.000 1.2994 0.10302 0.09709 -0.0374 0.0598 1.0000
16.250 1.2725 0.10987 0.10418 -0.0396 0.0602 1.0000
16.500 1.2444 0.11741 0.11194 -0.0427 0.0607 1.0000
16.750 1.2164 0.12570 0.12041 -0.0468 0.0613 1.0000
17.000 1.1915 0.13435 0.12920 -0.0513 0.0619 1.0000
17.250 1.1721 0.14301 0.13795 -0.0557 0.0626 1.0000
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