USA 29 AIRFOIL (usa29-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 29 AIRFOIL (usa29-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.1 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa29-il-1000000.txt Download as CSV file: xf-usa29-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.6833 0.08669 0.08468 -0.0713 1.0000 0.0183
-15.250 -0.7507 0.07478 0.07267 -0.0767 1.0000 0.0181
-15.000 -0.8135 0.06551 0.06332 -0.0797 1.0000 0.0176
-14.750 -0.9479 0.04285 0.04031 -0.1014 0.9908 0.0161
-14.500 -0.9656 0.03270 0.02981 -0.1109 0.9841 0.0163
-14.250 -0.9535 0.02834 0.02525 -0.1144 0.9807 0.0169
-14.000 -0.9348 0.02597 0.02275 -0.1158 0.9768 0.0176
-13.750 -0.9096 0.02413 0.02076 -0.1176 0.9746 0.0183
-13.500 -0.8841 0.02234 0.01881 -0.1193 0.9727 0.0193
-13.250 -0.8543 0.02128 0.01771 -0.1210 0.9714 0.0204
-13.000 -0.8213 0.02060 0.01698 -0.1228 0.9704 0.0215
-12.750 -0.7915 0.01998 0.01627 -0.1239 0.9679 0.0225
-12.500 -0.7685 0.01920 0.01541 -0.1238 0.9628 0.0235
-12.250 -0.7377 0.01879 0.01500 -0.1249 0.9597 0.0246
-12.000 -0.7043 0.01849 0.01467 -0.1264 0.9573 0.0255
-11.750 -0.6710 0.01821 0.01433 -0.1278 0.9541 0.0265
-11.500 -0.6484 0.01797 0.01402 -0.1269 0.9473 0.0272
-11.250 -0.6201 0.01758 0.01352 -0.1274 0.9423 0.0278
-11.000 -0.6002 0.01690 0.01280 -0.1264 0.9356 0.0289
-10.750 -0.5760 0.01667 0.01253 -0.1258 0.9293 0.0296
-10.500 -0.5454 0.01668 0.01251 -0.1264 0.9247 0.0304
-10.250 -0.5235 0.01650 0.01229 -0.1253 0.9175 0.0311
-10.000 -0.4981 0.01630 0.01202 -0.1249 0.9113 0.0319
-9.750 -0.4728 0.01623 0.01187 -0.1245 0.9050 0.0327
-9.500 -0.4491 0.01604 0.01160 -0.1237 0.8979 0.0331
-9.250 -0.4283 0.01545 0.01088 -0.1225 0.8911 0.0337
-9.000 -0.4115 0.01461 0.00994 -0.1207 0.8830 0.0347
-8.750 -0.3877 0.01432 0.00960 -0.1200 0.8766 0.0354
-8.500 -0.3634 0.01425 0.00950 -0.1193 0.8690 0.0362
-8.000 -0.3156 0.01382 0.00894 -0.1178 0.8550 0.0378
-7.750 -0.2918 0.01357 0.00860 -0.1170 0.8477 0.0385
-7.500 -0.2682 0.01333 0.00829 -0.1161 0.8405 0.0392
-7.250 -0.2438 0.01317 0.00804 -0.1153 0.8330 0.0398
-7.000 -0.2195 0.01298 0.00778 -0.1146 0.8256 0.0401
-6.750 -0.1974 0.01251 0.00721 -0.1134 0.8175 0.0406
-6.500 -0.1788 0.01160 0.00620 -0.1117 0.8096 0.0420
-6.250 -0.1560 0.01126 0.00579 -0.1107 0.8012 0.0428
-6.000 -0.1325 0.01097 0.00546 -0.1098 0.7925 0.0434
-5.750 -0.1090 0.01074 0.00515 -0.1088 0.7830 0.0441
-5.500 -0.0853 0.01051 0.00486 -0.1079 0.7720 0.0449
-5.250 -0.0616 0.01030 0.00459 -0.1070 0.7602 0.0457
-5.000 -0.0382 0.01013 0.00434 -0.1060 0.7463 0.0466
-4.750 -0.0154 0.00996 0.00407 -0.1048 0.7295 0.0473
-4.500 0.0072 0.00985 0.00386 -0.1036 0.7101 0.0479
-4.000 0.0520 0.00973 0.00351 -0.1011 0.6725 0.0488
-3.750 0.0738 0.00952 0.00318 -0.0998 0.6572 0.0499
-3.500 0.0967 0.00933 0.00290 -0.0987 0.6446 0.0515
-3.250 0.1209 0.00920 0.00271 -0.0979 0.6346 0.0530
-3.000 0.1449 0.00912 0.00256 -0.0970 0.6256 0.0547
-2.750 0.1700 0.00903 0.00242 -0.0964 0.6175 0.0561
-2.500 0.1944 0.00898 0.00231 -0.0956 0.6100 0.0575
-2.250 0.2200 0.00891 0.00220 -0.0951 0.6033 0.0588
-2.000 0.2446 0.00885 0.00210 -0.0943 0.5969 0.0620
-1.750 0.2699 0.00875 0.00201 -0.0938 0.5911 0.0680
-1.500 0.2947 0.00860 0.00196 -0.0931 0.5850 0.0953
-1.250 0.3187 0.00855 0.00192 -0.0923 0.5789 0.1139
-1.000 0.3441 0.00842 0.00187 -0.0918 0.5738 0.1323
-0.750 0.3679 0.00827 0.00184 -0.0910 0.5682 0.1747
-0.500 0.3913 0.00824 0.00184 -0.0900 0.5626 0.2005
-0.250 0.4163 0.00817 0.00183 -0.0894 0.5575 0.2190
0.000 0.4401 0.00813 0.00183 -0.0885 0.5521 0.2375
0.250 0.4629 0.00813 0.00186 -0.0875 0.5467 0.2591
0.500 0.4875 0.00809 0.00191 -0.0868 0.5419 0.2838
0.750 0.5117 0.00812 0.00197 -0.0860 0.5363 0.3031
1.000 0.5352 0.00820 0.00203 -0.0850 0.5308 0.3149
1.250 0.5607 0.00824 0.00207 -0.0845 0.5261 0.3238
1.500 0.5849 0.00830 0.00212 -0.0837 0.5206 0.3301
1.750 0.6079 0.00839 0.00219 -0.0827 0.5152 0.3359
2.000 0.6334 0.00845 0.00224 -0.0822 0.5102 0.3417
2.250 0.6570 0.00851 0.00232 -0.0813 0.5049 0.3476
2.500 0.6796 0.00863 0.00240 -0.0801 0.4996 0.3529
2.750 0.7045 0.00868 0.00246 -0.0795 0.4948 0.3568
3.000 0.7271 0.00873 0.00252 -0.0785 0.4895 0.3602
3.250 0.7477 0.00882 0.00259 -0.0769 0.4842 0.3632
3.500 0.7705 0.00886 0.00265 -0.0759 0.4797 0.3662
3.750 0.7917 0.00892 0.00271 -0.0745 0.4745 0.3689
4.000 0.8113 0.00903 0.00279 -0.0728 0.4694 0.3712
4.250 0.8337 0.00909 0.00286 -0.0717 0.4651 0.3731
4.500 0.8546 0.00912 0.00292 -0.0703 0.4601 0.3764
4.750 0.8744 0.00924 0.00304 -0.0686 0.4551 0.3792
5.000 0.8956 0.00933 0.00314 -0.0673 0.4506 0.3814
5.250 0.9170 0.00943 0.00325 -0.0661 0.4442 0.3850
5.500 0.9357 0.00959 0.00338 -0.0643 0.4367 0.3868
5.750 0.9566 0.00966 0.00348 -0.0629 0.4292 0.3901
6.000 0.9742 0.00983 0.00364 -0.0610 0.4217 0.3931
6.250 0.9956 0.00992 0.00376 -0.0598 0.4144 0.3956
6.500 1.0134 0.01011 0.00393 -0.0579 0.4061 0.3982
6.750 1.0344 0.01024 0.00407 -0.0567 0.3987 0.4008
7.000 1.0519 0.01043 0.00425 -0.0548 0.3897 0.4032
7.250 1.0706 0.01059 0.00442 -0.0531 0.3798 0.4051
7.500 1.0873 0.01082 0.00463 -0.0511 0.3663 0.4075
7.750 1.1019 0.01113 0.00489 -0.0488 0.3491 0.4096
8.000 1.1139 0.01156 0.00521 -0.0461 0.3251 0.4117
8.250 1.1182 0.01227 0.00572 -0.0421 0.2866 0.4135
8.500 1.1079 0.01360 0.00665 -0.0358 0.2204 0.4148
8.750 1.0862 0.01546 0.00805 -0.0281 0.1433 0.4156
9.000 1.0612 0.01763 0.00980 -0.0204 0.0638 0.4160
9.250 1.0548 0.01913 0.01114 -0.0158 0.0286 0.4178
9.500 1.0644 0.01990 0.01195 -0.0136 0.0241 0.4208
9.750 1.0742 0.02071 0.01279 -0.0115 0.0217 0.4234
10.000 1.0836 0.02158 0.01370 -0.0095 0.0199 0.4266
10.250 1.0953 0.02235 0.01453 -0.0078 0.0192 0.4303
10.500 1.1061 0.02322 0.01545 -0.0061 0.0183 0.4359
10.750 1.1140 0.02430 0.01660 -0.0043 0.0170 0.4440
11.000 1.1198 0.02559 0.01806 -0.0025 0.0160 0.4922
11.250 1.3005 0.02803 0.02167 -0.0394 0.0136 1.0000
11.500 1.3038 0.02961 0.02330 -0.0374 0.0132 1.0000
11.750 1.2980 0.03203 0.02582 -0.0349 0.0127 1.0000
12.000 1.2984 0.03408 0.02794 -0.0331 0.0126 1.0000
12.250 1.3061 0.03557 0.02948 -0.0319 0.0123 1.0000
12.500 1.3085 0.03761 0.03159 -0.0306 0.0121 1.0000
12.750 1.3082 0.03999 0.03406 -0.0293 0.0121 1.0000
13.000 1.3159 0.04166 0.03577 -0.0285 0.0115 1.0000
13.250 1.3174 0.04399 0.03816 -0.0276 0.0112 1.0000
13.500 1.3166 0.04663 0.04087 -0.0266 0.0110 1.0000
13.750 1.3209 0.04876 0.04304 -0.0260 0.0108 1.0000
14.000 1.3221 0.05127 0.04560 -0.0254 0.0106 1.0000
14.250 1.3198 0.05421 0.04861 -0.0247 0.0104 1.0000
14.500 1.3153 0.05741 0.05189 -0.0241 0.0103 1.0000
14.750 1.3119 0.06056 0.05511 -0.0236 0.0101 1.0000
15.000 1.2997 0.06476 0.05939 -0.0231 0.0098 1.0000
15.250 1.2946 0.06816 0.06287 -0.0227 0.0096 1.0000
15.500 1.2914 0.07137 0.06614 -0.0224 0.0096 1.0000
15.750 1.2938 0.07399 0.06882 -0.0222 0.0095 1.0000
16.000 1.2944 0.07686 0.07175 -0.0221 0.0094 1.0000
16.250 1.2958 0.07963 0.07460 -0.0220 0.0092 1.0000
16.500 1.2959 0.08256 0.07759 -0.0220 0.0091 1.0000
16.750 1.2961 0.08549 0.08058 -0.0219 0.0089 1.0000
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Polar data table (+)
Polar graphs
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