USA 29 AIRFOIL (usa29-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 29 AIRFOIL (usa29-il) Reynolds number: 500,000 Max Cl/Cd: 80.74 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa29-il-500000-n5.txt Download as CSV file: xf-usa29-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7524 0.05210 0.04943 -0.0971 0.9875 0.0194
-13.500 -0.8228 0.03548 0.03232 -0.1135 0.9722 0.0181
-13.250 -0.8188 0.03101 0.02761 -0.1162 0.9647 0.0191
-13.000 -0.7978 0.02798 0.02435 -0.1193 0.9616 0.0204
-12.750 -0.7680 0.02636 0.02263 -0.1219 0.9597 0.0220
-12.500 -0.7478 0.02527 0.02143 -0.1219 0.9534 0.0230
-12.250 -0.7217 0.02429 0.02028 -0.1229 0.9491 0.0249
-12.000 -0.6951 0.02314 0.01894 -0.1240 0.9457 0.0260
-11.750 -0.6712 0.02273 0.01851 -0.1239 0.9398 0.0269
-11.500 -0.6443 0.02234 0.01805 -0.1242 0.9345 0.0278
-11.250 -0.6147 0.02186 0.01747 -0.1252 0.9300 0.0289
-11.000 -0.5952 0.02129 0.01676 -0.1241 0.9219 0.0299
-10.750 -0.5701 0.02070 0.01599 -0.1241 0.9154 0.0309
-10.500 -0.5494 0.02014 0.01527 -0.1232 0.9080 0.0314
-10.250 -0.5281 0.01951 0.01457 -0.1225 0.9010 0.0322
-10.000 -0.5047 0.01919 0.01420 -0.1219 0.8943 0.0329
-9.750 -0.4813 0.01885 0.01378 -0.1213 0.8872 0.0335
-9.500 -0.4564 0.01865 0.01349 -0.1209 0.8807 0.0344
-9.250 -0.4336 0.01831 0.01306 -0.1201 0.8731 0.0353
-9.000 -0.4099 0.01797 0.01259 -0.1195 0.8662 0.0363
-8.750 -0.3871 0.01766 0.01214 -0.1187 0.8586 0.0372
-8.500 -0.3632 0.01737 0.01171 -0.1180 0.8514 0.0378
-8.250 -0.3406 0.01701 0.01123 -0.1170 0.8435 0.0381
-8.000 -0.3216 0.01610 0.01019 -0.1157 0.8361 0.0390
-7.750 -0.3005 0.01555 0.00956 -0.1145 0.8276 0.0396
-7.500 -0.2779 0.01512 0.00903 -0.1135 0.8201 0.0401
-7.250 -0.2555 0.01472 0.00854 -0.1125 0.8114 0.0405
-7.000 -0.2324 0.01437 0.00810 -0.1116 0.8031 0.0411
-6.750 -0.2094 0.01403 0.00766 -0.1106 0.7938 0.0417
-6.500 -0.1864 0.01370 0.00724 -0.1097 0.7843 0.0423
-6.250 -0.1632 0.01340 0.00683 -0.1087 0.7741 0.0428
-6.000 -0.1399 0.01314 0.00649 -0.1078 0.7623 0.0436
-5.750 -0.1166 0.01290 0.00615 -0.1068 0.7497 0.0444
-5.500 -0.0936 0.01265 0.00579 -0.1058 0.7358 0.0449
-5.250 -0.0707 0.01244 0.00546 -0.1047 0.7198 0.0454
-5.000 -0.0484 0.01227 0.00517 -0.1035 0.7018 0.0459
-4.750 -0.0262 0.01213 0.00489 -0.1022 0.6841 0.0462
-4.500 -0.0036 0.01202 0.00466 -0.1011 0.6684 0.0465
-4.250 0.0182 0.01176 0.00429 -0.0998 0.6549 0.0475
-4.000 0.0408 0.01155 0.00399 -0.0987 0.6433 0.0487
-3.750 0.0642 0.01140 0.00376 -0.0977 0.6335 0.0496
-3.500 0.0883 0.01127 0.00356 -0.0970 0.6247 0.0507
-3.250 0.1125 0.01117 0.00339 -0.0962 0.6168 0.0520
-3.000 0.1371 0.01107 0.00323 -0.0955 0.6092 0.0534
-2.750 0.1615 0.01100 0.00309 -0.0947 0.6026 0.0549
-2.500 0.1868 0.01092 0.00296 -0.0941 0.5963 0.0559
-2.250 0.2115 0.01087 0.00284 -0.0934 0.5898 0.0569
-2.000 0.2365 0.01079 0.00273 -0.0928 0.5840 0.0597
-1.750 0.2615 0.01070 0.00264 -0.0922 0.5779 0.0637
-1.500 0.2860 0.01061 0.00257 -0.0915 0.5725 0.0718
-1.250 0.3108 0.01048 0.00252 -0.0909 0.5674 0.1005
-1.000 0.3358 0.01044 0.00248 -0.0903 0.5616 0.1102
-0.750 0.3598 0.01040 0.00243 -0.0895 0.5560 0.1219
-0.250 0.4085 0.01019 0.00240 -0.0881 0.5459 0.1757
0.000 0.4321 0.01018 0.00240 -0.0872 0.5406 0.1965
0.250 0.4562 0.01014 0.00241 -0.0865 0.5355 0.2143
0.500 0.4799 0.01012 0.00243 -0.0856 0.5300 0.2307
0.750 0.5028 0.01011 0.00248 -0.0846 0.5251 0.2535
1.000 0.5263 0.01012 0.00258 -0.0837 0.5205 0.2834
1.250 0.5502 0.01016 0.00266 -0.0829 0.5149 0.3005
1.500 0.5734 0.01024 0.00272 -0.0819 0.5096 0.3109
1.750 0.5973 0.01031 0.00279 -0.0811 0.5049 0.3209
2.000 0.6211 0.01038 0.00287 -0.0802 0.4998 0.3290
2.250 0.6439 0.01048 0.00294 -0.0792 0.4946 0.3361
2.500 0.6670 0.01057 0.00304 -0.0782 0.4899 0.3440
2.750 0.6903 0.01064 0.00311 -0.0773 0.4846 0.3481
3.000 0.7126 0.01073 0.00318 -0.0762 0.4798 0.3521
3.250 0.7344 0.01081 0.00327 -0.0749 0.4753 0.3549
3.500 0.7564 0.01088 0.00336 -0.0738 0.4701 0.3587
3.750 0.7770 0.01097 0.00344 -0.0723 0.4652 0.3620
4.000 0.7968 0.01108 0.00353 -0.0707 0.4608 0.3652
4.250 0.8184 0.01114 0.00363 -0.0694 0.4561 0.3682
4.500 0.8387 0.01122 0.00374 -0.0680 0.4512 0.3707
4.750 0.8584 0.01136 0.00387 -0.0663 0.4467 0.3751
5.000 0.8797 0.01147 0.00401 -0.0651 0.4423 0.3789
5.250 0.9005 0.01157 0.00415 -0.0637 0.4375 0.3817
5.500 0.9201 0.01170 0.00430 -0.0622 0.4330 0.3847
5.750 0.9401 0.01185 0.00447 -0.0607 0.4290 0.3877
6.000 0.9614 0.01197 0.00464 -0.0595 0.4247 0.3909
6.250 0.9802 0.01214 0.00482 -0.0579 0.4183 0.3934
6.500 0.9962 0.01234 0.00501 -0.0557 0.4064 0.3952
6.750 1.0118 0.01256 0.00523 -0.0534 0.3950 0.3970
7.000 1.0269 0.01281 0.00547 -0.0512 0.3843 0.3992
7.250 1.0452 0.01301 0.00570 -0.0495 0.3748 0.4011
7.500 1.0605 0.01330 0.00597 -0.0474 0.3631 0.4031
7.750 1.0737 0.01366 0.00630 -0.0449 0.3467 0.4047
8.000 1.0847 0.01412 0.00669 -0.0421 0.3264 0.4068
8.500 1.0980 0.01545 0.00779 -0.0354 0.2709 0.4100
8.750 1.0949 0.01660 0.00871 -0.0308 0.2265 0.4117
9.000 1.0800 0.01840 0.01014 -0.0248 0.1641 0.4132
9.250 1.0533 0.02095 0.01225 -0.0178 0.0855 0.4143
9.500 1.0391 0.02309 0.01416 -0.0130 0.0349 0.4158
9.750 1.0454 0.02418 0.01528 -0.0107 0.0270 0.4185
10.000 1.0545 0.02516 0.01630 -0.0089 0.0235 0.4214
10.250 1.0632 0.02619 0.01739 -0.0071 0.0209 0.4250
10.500 1.0700 0.02741 0.01866 -0.0053 0.0186 0.4286
10.750 1.0794 0.02850 0.01983 -0.0038 0.0177 0.4338
11.000 1.0875 0.02972 0.02114 -0.0024 0.0166 0.4430
11.250 1.0958 0.03095 0.02254 -0.0012 0.0158 0.4835
11.750 1.2502 0.03645 0.02927 -0.0318 0.0121 1.0000
12.000 1.2541 0.03832 0.03122 -0.0305 0.0117 1.0000
12.250 1.2572 0.04035 0.03331 -0.0293 0.0112 1.0000
12.500 1.2584 0.04265 0.03569 -0.0282 0.0111 1.0000
12.750 1.2583 0.04515 0.03825 -0.0272 0.0108 1.0000
13.000 1.2572 0.04782 0.04099 -0.0264 0.0104 1.0000
13.250 1.2531 0.05090 0.04415 -0.0255 0.0101 1.0000
13.500 1.2579 0.05304 0.04637 -0.0249 0.0098 1.0000
13.750 1.2584 0.05568 0.04909 -0.0244 0.0097 1.0000
14.000 1.2548 0.05887 0.05237 -0.0238 0.0095 1.0000
14.250 1.2554 0.06160 0.05517 -0.0234 0.0092 1.0000
14.500 1.2550 0.06449 0.05814 -0.0231 0.0089 1.0000
14.750 1.2544 0.06742 0.06114 -0.0229 0.0088 1.0000
15.000 1.2523 0.07061 0.06441 -0.0227 0.0086 1.0000
15.250 1.2502 0.07383 0.06770 -0.0225 0.0085 1.0000
15.500 1.2510 0.07672 0.07066 -0.0225 0.0083 1.0000
15.750 1.2490 0.07999 0.07399 -0.0225 0.0081 1.0000
16.000 1.2477 0.08321 0.07728 -0.0226 0.0080 1.0000
16.250 1.2455 0.08657 0.08070 -0.0228 0.0079 1.0000
16.500 1.2425 0.09006 0.08424 -0.0230 0.0077 1.0000
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