74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: 74-130 WP2 (fx74130wp2-il) Reynolds number: 500,000 Max Cl/Cd: 125.81 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74130wp2-il-500000.txt Download as CSV file: xf-fx74130wp2-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: 74-130 WP2
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1104 0.08725 0.08411 -0.0884 0.7824 0.0146
-10.250 -0.1080 0.08359 0.08044 -0.0898 0.7816 0.0151
-10.000 -0.1059 0.07986 0.07672 -0.0913 0.7809 0.0155
-9.750 -0.1053 0.07588 0.07275 -0.0929 0.7801 0.0164
-9.500 -0.1051 0.07186 0.06874 -0.0949 0.7794 0.0171
-9.250 -0.1051 0.06790 0.06478 -0.0967 0.7786 0.0173
-9.000 -0.1039 0.06416 0.06105 -0.0996 0.7777 0.0180
-8.750 -0.1050 0.06000 0.05691 -0.1022 0.7769 0.0181
-8.500 -0.1087 0.05529 0.05223 -0.1055 0.7761 0.0181
-8.250 -0.1177 0.05033 0.04726 -0.1096 0.7750 0.0181
-8.000 -0.1284 0.04665 0.04355 -0.1110 0.7736 0.0181
-7.750 -0.1416 0.04378 0.04064 -0.1102 0.7720 0.0181
-7.500 -0.1690 0.05353 0.05005 -0.1162 0.7733 0.0181
-7.250 -0.1657 0.05060 0.04698 -0.1156 0.7718 0.0182
-7.000 -0.1605 0.04772 0.04394 -0.1148 0.7704 0.0182
-6.750 -0.1531 0.04491 0.04094 -0.1139 0.7692 0.0182
-6.500 -0.1623 0.03779 0.03357 -0.1127 0.7680 0.0192
-6.250 -0.1479 0.03558 0.03126 -0.1123 0.7670 0.0198
-6.000 -0.1316 0.03375 0.02932 -0.1119 0.7661 0.0205
-5.750 -0.1139 0.03179 0.02719 -0.1113 0.7652 0.0213
-5.500 -0.0947 0.02991 0.02510 -0.1106 0.7643 0.0227
-5.250 -0.0733 0.02824 0.02318 -0.1099 0.7633 0.0247
-5.000 -0.0449 0.02900 0.02371 -0.1091 0.7622 0.0271
-4.750 -0.0313 0.02408 0.01837 -0.1081 0.7610 0.0289
-4.500 -0.0080 0.02243 0.01665 -0.1080 0.7599 0.0305
-4.250 0.0200 0.01934 0.01299 -0.1061 0.7589 0.0189
-4.000 0.0454 0.01712 0.01062 -0.1055 0.7578 0.0160
-3.750 0.0713 0.01592 0.00929 -0.1050 0.7568 0.0160
-3.500 0.0969 0.01509 0.00838 -0.1046 0.7557 0.0164
-3.250 0.1226 0.01447 0.00770 -0.1043 0.7546 0.0171
-3.000 0.1497 0.01430 0.00748 -0.1043 0.7536 0.0183
-2.750 0.1739 0.01347 0.00658 -0.1039 0.7526 0.0191
-2.500 0.1997 0.01298 0.00602 -0.1037 0.7518 0.0204
-2.250 0.2265 0.01273 0.00572 -0.1037 0.7510 0.0237
-2.000 0.2499 0.01174 0.00540 -0.1036 0.7501 0.2241
-1.750 0.2691 0.01017 0.00534 -0.1035 0.7490 0.6584
-1.500 0.2904 0.01049 0.00602 -0.1016 0.7475 0.8026
-1.250 0.3134 0.01084 0.00640 -0.1002 0.7460 0.8256
-1.000 0.3364 0.01114 0.00670 -0.0989 0.7447 0.8411
-0.750 0.3568 0.01146 0.00703 -0.0969 0.7435 0.8589
-0.500 0.3773 0.01166 0.00724 -0.0950 0.7422 0.8709
-0.250 0.4007 0.01175 0.00732 -0.0939 0.7410 0.8787
0.000 0.4253 0.01185 0.00738 -0.0932 0.7398 0.8850
0.250 0.4524 0.01193 0.00742 -0.0933 0.7389 0.8898
0.500 0.4780 0.01196 0.00744 -0.0930 0.7379 0.8927
0.750 0.5053 0.01204 0.00748 -0.0931 0.7370 0.8953
1.000 0.5329 0.01218 0.00760 -0.0934 0.7359 0.8978
1.250 0.5583 0.01231 0.00777 -0.0935 0.7336 0.9001
1.500 0.5859 0.01241 0.00788 -0.0939 0.7312 0.9020
1.750 0.6135 0.01242 0.00789 -0.0942 0.7292 0.9035
2.000 0.6412 0.01240 0.00789 -0.0945 0.7276 0.9049
2.250 0.6693 0.01239 0.00788 -0.0948 0.7262 0.9063
2.500 0.6981 0.01239 0.00788 -0.0953 0.7249 0.9076
2.750 0.7282 0.01235 0.00784 -0.0960 0.7236 0.9087
3.000 0.7577 0.01237 0.00787 -0.0966 0.7221 0.9101
3.250 0.7816 0.01248 0.00806 -0.0964 0.7181 0.9117
3.500 0.8106 0.01241 0.00803 -0.0969 0.7153 0.9128
3.750 0.8415 0.01220 0.00783 -0.0977 0.7128 0.9138
4.000 0.8738 0.01195 0.00760 -0.0987 0.7106 0.9149
4.250 0.9056 0.01173 0.00738 -0.0996 0.7079 0.9159
4.500 0.9313 0.01154 0.00728 -0.0995 0.7021 0.9170
4.750 0.9636 0.01100 0.00675 -0.1002 0.6976 0.9178
5.000 0.9921 0.01060 0.00641 -0.1003 0.6913 0.9189
5.250 1.0210 0.01018 0.00603 -0.1005 0.6846 0.9200
5.500 1.0473 0.00975 0.00567 -0.1002 0.6745 0.9217
5.750 1.0736 0.00943 0.00541 -0.0999 0.6632 0.9234
6.000 1.0999 0.00927 0.00534 -0.0998 0.6525 0.9249
6.250 1.1247 0.00916 0.00531 -0.0994 0.6346 0.9266
6.500 1.1461 0.00911 0.00518 -0.0982 0.5942 0.9285
6.750 1.1486 0.00981 0.00545 -0.0936 0.5120 0.9317
7.000 1.1390 0.01091 0.00619 -0.0870 0.4420 0.9371
7.250 1.1238 0.01197 0.00701 -0.0796 0.3869 0.9448
7.500 1.1075 0.01326 0.00809 -0.0727 0.3371 0.9572
7.750 1.1011 0.01515 0.00968 -0.0693 0.2724 1.0000
8.000 1.0968 0.01714 0.01133 -0.0663 0.2103 1.0000
8.250 1.0939 0.01910 0.01294 -0.0635 0.1480 1.0000
8.500 1.0948 0.02085 0.01438 -0.0611 0.0973 1.0000
8.750 1.0992 0.02242 0.01570 -0.0591 0.0607 1.0000
9.000 1.1080 0.02373 0.01689 -0.0576 0.0417 1.0000
9.250 1.1192 0.02488 0.01800 -0.0563 0.0321 1.0000
9.500 1.1322 0.02592 0.01905 -0.0552 0.0261 1.0000
9.750 1.1439 0.02707 0.02023 -0.0540 0.0205 1.0000
10.000 1.1497 0.02869 0.02187 -0.0520 0.0147 1.0000
10.250 1.1617 0.02987 0.02309 -0.0509 0.0120 1.0000
10.500 1.1631 0.03189 0.02519 -0.0487 0.0100 1.0000
10.750 1.1702 0.03352 0.02694 -0.0471 0.0095 1.0000
11.000 1.1795 0.03501 0.02852 -0.0458 0.0089 1.0000
11.250 1.1878 0.03661 0.03022 -0.0444 0.0085 1.0000
11.500 1.1963 0.03826 0.03197 -0.0431 0.0082 1.0000
11.750 1.2061 0.03983 0.03362 -0.0420 0.0078 1.0000
12.000 1.2163 0.04136 0.03523 -0.0410 0.0074 1.0000
12.250 1.2260 0.04299 0.03693 -0.0401 0.0070 1.0000
12.500 1.2341 0.04484 0.03885 -0.0391 0.0066 1.0000
12.750 1.2418 0.04703 0.04117 -0.0378 0.0064 1.0000
13.000 1.2517 0.04946 0.04379 -0.0365 0.0063 1.0000
13.250 1.2616 0.05242 0.04700 -0.0352 0.0061 1.0000
13.500 1.2676 0.05492 0.04972 -0.0343 0.0061 1.0000
13.750 1.2708 0.05753 0.05253 -0.0335 0.0060 1.0000
14.000 1.2711 0.06079 0.05602 -0.0326 0.0060 1.0000
14.250 1.2684 0.06432 0.05978 -0.0318 0.0059 1.0000
14.500 1.2623 0.06836 0.06405 -0.0312 0.0059 1.0000
14.750 1.2524 0.07302 0.06896 -0.0308 0.0059 1.0000
15.000 1.2391 0.07828 0.07446 -0.0309 0.0059 1.0000
15.250 1.2242 0.08384 0.08026 -0.0314 0.0059 1.0000
15.500 1.2063 0.09019 0.08683 -0.0326 0.0060 1.0000
15.750 1.1867 0.09713 0.09399 -0.0344 0.0060 1.0000
16.000 1.1665 0.10456 0.10163 -0.0371 0.0060 1.0000
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Polar data table (+)
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