USA 29 AIRFOIL (usa29-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: USA 29 AIRFOIL (usa29-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.52 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa29-il-1000000-n5.txt Download as CSV file: xf-usa29-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 29 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.6244 0.09190 0.08981 -0.0693 0.9995 0.0125
-15.000 -0.7390 0.06830 0.06593 -0.0864 0.9973 0.0113
-14.750 -0.8357 0.04966 0.04703 -0.1034 0.9867 0.0103
-14.500 -0.9143 0.03279 0.02969 -0.1185 0.9707 0.0096
-14.250 -0.9059 0.02781 0.02445 -0.1226 0.9648 0.0100
-14.000 -0.8849 0.02445 0.02086 -0.1259 0.9612 0.0105
-13.750 -0.8647 0.02234 0.01859 -0.1272 0.9565 0.0112
-13.500 -0.8451 0.02098 0.01710 -0.1273 0.9505 0.0120
-13.250 -0.8206 0.01987 0.01585 -0.1280 0.9455 0.0127
-13.000 -0.8050 0.01882 0.01471 -0.1268 0.9374 0.0140
-12.750 -0.7843 0.01793 0.01371 -0.1263 0.9308 0.0154
-12.500 -0.7663 0.01720 0.01292 -0.1250 0.9237 0.0172
-12.250 -0.7455 0.01659 0.01223 -0.1242 0.9162 0.0191
-12.000 -0.7245 0.01609 0.01166 -0.1232 0.9089 0.0209
-11.750 -0.7016 0.01572 0.01126 -0.1225 0.9008 0.0227
-11.500 -0.6790 0.01537 0.01084 -0.1217 0.8924 0.0241
-11.000 -0.6341 0.01471 0.00999 -0.1199 0.8743 0.0259
-10.750 -0.6108 0.01443 0.00965 -0.1191 0.8668 0.0269
-10.500 -0.5867 0.01422 0.00940 -0.1185 0.8592 0.0278
-10.250 -0.5627 0.01403 0.00914 -0.1178 0.8518 0.0287
-10.000 -0.5384 0.01383 0.00889 -0.1171 0.8447 0.0296
-9.750 -0.5150 0.01360 0.00857 -0.1163 0.8375 0.0302
-9.500 -0.4911 0.01337 0.00827 -0.1155 0.8301 0.0307
-9.250 -0.4669 0.01320 0.00801 -0.1148 0.8233 0.0312
-9.000 -0.4431 0.01296 0.00769 -0.1141 0.8163 0.0315
-8.750 -0.4215 0.01258 0.00723 -0.1129 0.8085 0.0324
-8.500 -0.3970 0.01239 0.00702 -0.1123 0.8015 0.0332
-8.250 -0.3717 0.01231 0.00690 -0.1117 0.7934 0.0341
-8.000 -0.3463 0.01222 0.00678 -0.1112 0.7855 0.0349
-7.750 -0.3226 0.01202 0.00650 -0.1104 0.7764 0.0355
-7.500 -0.2989 0.01179 0.00619 -0.1095 0.7662 0.0359
-7.250 -0.2756 0.01156 0.00588 -0.1085 0.7555 0.0363
-7.000 -0.2524 0.01138 0.00560 -0.1076 0.7419 0.0367
-6.750 -0.2294 0.01122 0.00534 -0.1065 0.7258 0.0371
-6.500 -0.2067 0.01108 0.00508 -0.1054 0.7061 0.0374
-6.250 -0.1847 0.01097 0.00485 -0.1041 0.6840 0.0377
-6.000 -0.1625 0.01089 0.00464 -0.1029 0.6640 0.0379
-5.750 -0.1390 0.01083 0.00449 -0.1020 0.6483 0.0381
-5.250 -0.0932 0.01039 0.00386 -0.0999 0.6247 0.0397
-5.000 -0.0690 0.01025 0.00365 -0.0991 0.6163 0.0403
-4.750 -0.0441 0.01012 0.00347 -0.0985 0.6087 0.0409
-4.500 -0.0194 0.01001 0.00331 -0.0978 0.6020 0.0415
-4.250 0.0060 0.00990 0.00315 -0.0972 0.5950 0.0422
-4.000 0.0309 0.00982 0.00302 -0.0966 0.5885 0.0430
-3.750 0.0565 0.00971 0.00288 -0.0961 0.5831 0.0435
-3.500 0.0821 0.00963 0.00275 -0.0955 0.5774 0.0443
-3.000 0.1330 0.00949 0.00253 -0.0944 0.5663 0.0456
-2.750 0.1586 0.00943 0.00245 -0.0939 0.5608 0.0461
-2.250 0.2096 0.00930 0.00225 -0.0928 0.5510 0.0479
-2.000 0.2350 0.00922 0.00215 -0.0923 0.5454 0.0498
-1.750 0.2599 0.00917 0.00207 -0.0916 0.5400 0.0515
-1.500 0.2856 0.00911 0.00200 -0.0911 0.5355 0.0531
-1.250 0.3110 0.00907 0.00194 -0.0906 0.5304 0.0549
-1.000 0.3358 0.00906 0.00190 -0.0899 0.5250 0.0566
-0.750 0.3610 0.00901 0.00186 -0.0893 0.5202 0.0627
-0.500 0.3856 0.00889 0.00183 -0.0887 0.5148 0.0891
-0.250 0.4099 0.00886 0.00182 -0.0879 0.5098 0.1014
0.000 0.4347 0.00885 0.00181 -0.0873 0.5053 0.1078
0.250 0.4593 0.00882 0.00180 -0.0866 0.4999 0.1165
0.500 0.4831 0.00882 0.00180 -0.0857 0.4942 0.1250
0.750 0.5060 0.00870 0.00180 -0.0847 0.4898 0.1669
1.000 0.5297 0.00865 0.00182 -0.0839 0.4850 0.1924
1.250 0.5527 0.00865 0.00184 -0.0829 0.4798 0.2083
1.500 0.5757 0.00865 0.00187 -0.0819 0.4751 0.2212
1.750 0.5987 0.00863 0.00191 -0.0809 0.4700 0.2426
2.000 0.6207 0.00862 0.00197 -0.0797 0.4653 0.2705
2.250 0.6429 0.00866 0.00204 -0.0785 0.4605 0.2883
2.500 0.6663 0.00869 0.00212 -0.0776 0.4563 0.3067
2.750 0.6885 0.00875 0.00219 -0.0764 0.4509 0.3164
3.000 0.7092 0.00883 0.00226 -0.0749 0.4463 0.3249
3.250 0.7313 0.00888 0.00234 -0.0737 0.4422 0.3315
3.500 0.7529 0.00895 0.00240 -0.0724 0.4373 0.3360
3.750 0.7739 0.00903 0.00248 -0.0710 0.4326 0.3385
4.000 0.7951 0.00911 0.00257 -0.0696 0.4287 0.3414
4.250 0.8171 0.00918 0.00266 -0.0685 0.4243 0.3444
4.500 0.8385 0.00928 0.00276 -0.0672 0.4199 0.3466
4.750 0.8589 0.00941 0.00288 -0.0657 0.4152 0.3495
5.000 0.8812 0.00950 0.00299 -0.0647 0.4118 0.3515
5.250 0.9028 0.00959 0.00311 -0.0635 0.4076 0.3552
5.500 0.9233 0.00973 0.00326 -0.0620 0.4025 0.3587
5.750 0.9437 0.00988 0.00342 -0.0607 0.3951 0.3642
6.000 0.9611 0.01012 0.00359 -0.0587 0.3800 0.3657
6.250 0.9784 0.01034 0.00378 -0.0568 0.3682 0.3680
6.500 0.9975 0.01052 0.00396 -0.0552 0.3576 0.3698
6.750 1.0160 0.01072 0.00415 -0.0535 0.3479 0.3717
7.000 1.0317 0.01103 0.00440 -0.0513 0.3315 0.3744
7.250 1.0468 0.01136 0.00467 -0.0491 0.3142 0.3763
7.500 1.0598 0.01178 0.00500 -0.0466 0.2943 0.3779
7.750 1.0630 0.01257 0.00556 -0.0424 0.2518 0.3786
8.000 1.0662 0.01338 0.00617 -0.0383 0.2154 0.3796
8.500 1.0234 0.01716 0.00908 -0.0231 0.0549 0.3804
8.750 1.0257 0.01819 0.01002 -0.0196 0.0285 0.3814
9.000 1.0374 0.01882 0.01066 -0.0175 0.0231 0.3829
9.250 1.0495 0.01945 0.01130 -0.0156 0.0196 0.3842
9.500 1.0622 0.02009 0.01197 -0.0138 0.0171 0.3858
9.750 1.0749 0.02075 0.01266 -0.0121 0.0161 0.3876
10.000 1.0865 0.02149 0.01342 -0.0103 0.0146 0.3888
10.250 1.0983 0.02225 0.01421 -0.0086 0.0133 0.3910
10.500 1.1098 0.02306 0.01506 -0.0070 0.0127 0.3924
10.750 1.1211 0.02391 0.01595 -0.0055 0.0121 0.3937
11.000 1.1309 0.02488 0.01696 -0.0038 0.0113 0.3957
11.250 1.1405 0.02590 0.01803 -0.0023 0.0109 0.3974
11.500 1.1493 0.02704 0.01921 -0.0008 0.0100 0.3999
11.750 1.1595 0.02812 0.02034 0.0004 0.0098 0.4020
12.000 1.1691 0.02927 0.02154 0.0016 0.0095 0.4043
12.250 1.1784 0.03051 0.02283 0.0027 0.0089 0.4068
12.750 1.1926 0.03349 0.02594 0.0049 0.0086 0.4128
13.000 1.2000 0.03503 0.02753 0.0058 0.0083 0.4173
13.500 1.2099 0.03877 0.03141 0.0074 0.0075 0.4324
14.000 1.3610 0.04520 0.03924 -0.0243 0.0066 0.9992
14.250 1.3747 0.04796 0.04207 -0.0264 0.0065 1.0000
14.500 1.3773 0.05028 0.04445 -0.0257 0.0062 1.0000
14.750 1.3789 0.05274 0.04696 -0.0252 0.0061 1.0000
15.000 1.3783 0.05548 0.04977 -0.0246 0.0060 1.0000
15.250 1.3806 0.05792 0.05225 -0.0242 0.0058 1.0000
15.500 1.3770 0.06110 0.05552 -0.0237 0.0058 1.0000
15.750 1.3743 0.06421 0.05869 -0.0234 0.0056 1.0000
16.000 1.3739 0.06706 0.06160 -0.0232 0.0055 1.0000
16.250 1.3656 0.07096 0.06559 -0.0230 0.0054 1.0000
16.500 1.3648 0.07399 0.06869 -0.0229 0.0053 1.0000
16.750 1.3650 0.07692 0.07168 -0.0229 0.0052 1.0000
17.000 1.3639 0.08002 0.07485 -0.0230 0.0051 1.0000
17.250 1.3561 0.08406 0.07898 -0.0232 0.0052 1.0000
17.500 1.3544 0.08733 0.08232 -0.0234 0.0051 1.0000
17.750 1.3567 0.09005 0.08510 -0.0236 0.0050 1.0000
18.000 1.3499 0.09412 0.08926 -0.0240 0.0049 1.0000
18.250 1.3499 0.09720 0.09241 -0.0244 0.0048 1.0000
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