USA 29 AIRFOIL (usa29-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 29 AIRFOIL (usa29-il) Reynolds number: 500,000 Max Cl/Cd: 89.96 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa29-il-500000.txt Download as CSV file: xf-usa29-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2422 0.10995 0.10765 -0.0622 0.9896 0.0370
-11.000 -0.5381 0.03603 0.03303 -0.1216 0.9659 0.0323
-10.750 -0.5242 0.03305 0.02963 -0.1241 0.9602 0.0333
-10.500 -0.5089 0.02949 0.02585 -0.1262 0.9571 0.0345
-10.250 -0.4736 0.02934 0.02573 -0.1283 0.9557 0.0355
-10.000 -0.4516 0.02898 0.02536 -0.1278 0.9498 0.0365
-9.750 -0.4298 0.02772 0.02394 -0.1281 0.9448 0.0376
-9.500 -0.4059 0.02632 0.02228 -0.1287 0.9409 0.0390
-9.250 -0.3894 0.02575 0.02149 -0.1271 0.9334 0.0399
-9.000 -0.3784 0.02337 0.01877 -0.1256 0.9268 0.0411
-8.750 -0.3594 0.02217 0.01752 -0.1246 0.9209 0.0422
-8.500 -0.3396 0.02153 0.01680 -0.1235 0.9140 0.0432
-8.250 -0.3134 0.02097 0.01618 -0.1235 0.9093 0.0446
-8.000 -0.2960 0.02031 0.01539 -0.1216 0.9014 0.0456
-7.750 -0.2735 0.01956 0.01447 -0.1208 0.8953 0.0468
-7.500 -0.2526 0.01898 0.01373 -0.1195 0.8882 0.0477
-7.250 -0.2300 0.01851 0.01310 -0.1185 0.8812 0.0484
-7.000 -0.2067 0.01809 0.01252 -0.1175 0.8743 0.0489
-6.750 -0.1907 0.01605 0.01026 -0.1157 0.8662 0.0503
-6.500 -0.1678 0.01520 0.00933 -0.1148 0.8590 0.0515
-6.250 -0.1453 0.01462 0.00866 -0.1138 0.8506 0.0524
-6.000 -0.1214 0.01410 0.00805 -0.1130 0.8426 0.0533
-5.750 -0.0977 0.01362 0.00747 -0.1120 0.8338 0.0543
-5.500 -0.0742 0.01322 0.00699 -0.1111 0.8247 0.0554
-5.250 -0.0492 0.01285 0.00650 -0.1104 0.8157 0.0566
-5.000 -0.0264 0.01248 0.00606 -0.1093 0.8051 0.0574
-4.750 -0.0025 0.01215 0.00563 -0.1083 0.7947 0.0582
-4.500 0.0219 0.01189 0.00526 -0.1075 0.7835 0.0588
-4.250 0.0439 0.01148 0.00476 -0.1061 0.7705 0.0600
-4.000 0.0661 0.01111 0.00431 -0.1049 0.7567 0.0616
-3.750 0.0890 0.01085 0.00398 -0.1037 0.7419 0.0637
-3.500 0.1121 0.01067 0.00372 -0.1026 0.7263 0.0659
-3.250 0.1354 0.01053 0.00347 -0.1016 0.7106 0.0679
-3.000 0.1588 0.01042 0.00326 -0.1005 0.6955 0.0699
-2.750 0.1822 0.01029 0.00307 -0.0995 0.6817 0.0742
-2.500 0.2060 0.01020 0.00294 -0.0986 0.6695 0.0815
-2.250 0.2299 0.01010 0.00283 -0.0977 0.6590 0.1002
-2.000 0.2543 0.00996 0.00272 -0.0970 0.6493 0.1235
-1.750 0.2783 0.00980 0.00264 -0.0962 0.6407 0.1580
-1.500 0.3024 0.00971 0.00263 -0.0955 0.6322 0.1962
-1.250 0.3267 0.00969 0.00261 -0.0947 0.6250 0.2195
-1.000 0.3509 0.00965 0.00263 -0.0940 0.6178 0.2411
-0.750 0.3752 0.00970 0.00265 -0.0932 0.6112 0.2612
-0.500 0.3997 0.00971 0.00272 -0.0925 0.6046 0.2815
-0.250 0.4242 0.00980 0.00281 -0.0917 0.5981 0.2992
0.000 0.4493 0.00992 0.00290 -0.0911 0.5922 0.3135
0.250 0.4741 0.01001 0.00297 -0.0904 0.5860 0.3246
0.500 0.4988 0.01014 0.00306 -0.0897 0.5802 0.3324
0.750 0.5235 0.01026 0.00314 -0.0890 0.5743 0.3413
1.000 0.5477 0.01034 0.00322 -0.0882 0.5686 0.3474
1.250 0.5725 0.01050 0.00331 -0.0875 0.5633 0.3546
1.500 0.5964 0.01056 0.00339 -0.0867 0.5577 0.3609
1.750 0.6200 0.01066 0.00348 -0.0858 0.5519 0.3679
2.000 0.6444 0.01080 0.00355 -0.0851 0.5467 0.3740
2.250 0.6680 0.01080 0.00361 -0.0842 0.5413 0.3784
2.500 0.6915 0.01087 0.00367 -0.0833 0.5358 0.3831
2.750 0.7157 0.01101 0.00373 -0.0826 0.5307 0.3870
3.000 0.7386 0.01098 0.00377 -0.0816 0.5253 0.3906
3.250 0.7618 0.01102 0.00383 -0.0807 0.5201 0.3943
3.500 0.7854 0.01115 0.00391 -0.0799 0.5150 0.3988
3.750 0.8078 0.01117 0.00399 -0.0788 0.5099 0.4033
4.000 0.8297 0.01120 0.00405 -0.0776 0.5046 0.4081
4.250 0.8530 0.01132 0.00414 -0.0767 0.4998 0.4122
4.500 0.8746 0.01137 0.00424 -0.0755 0.4947 0.4159
4.750 0.8957 0.01140 0.00431 -0.0742 0.4896 0.4194
5.000 0.9176 0.01151 0.00441 -0.0731 0.4847 0.4227
5.250 0.9380 0.01156 0.00453 -0.0716 0.4800 0.4262
5.500 0.9572 0.01163 0.00463 -0.0699 0.4749 0.4304
5.750 0.9760 0.01172 0.00472 -0.0681 0.4696 0.4352
6.000 0.9916 0.01176 0.00483 -0.0656 0.4628 0.4394
6.250 1.0064 0.01188 0.00494 -0.0630 0.4547 0.4435
6.500 1.0225 0.01198 0.00510 -0.0608 0.4468 0.4467
6.750 1.0377 0.01213 0.00525 -0.0583 0.4390 0.4506
7.000 1.0549 0.01224 0.00544 -0.0563 0.4317 0.4554
7.250 1.0700 0.01242 0.00563 -0.0540 0.4235 0.4612
7.500 1.0860 0.01254 0.00585 -0.0518 0.4147 0.4737
7.750 1.0931 0.01241 0.00608 -0.0479 0.4060 0.6589
8.000 1.2613 0.01402 0.00794 -0.0814 0.2972 0.9998
8.250 1.2439 0.01564 0.00908 -0.0739 0.2214 1.0000
8.500 1.2142 0.01795 0.01084 -0.0649 0.1333 1.0000
8.750 1.1880 0.02039 0.01286 -0.0573 0.0554 1.0000
9.000 1.1835 0.02193 0.01431 -0.0530 0.0346 1.0000
9.250 1.1887 0.02303 0.01545 -0.0502 0.0299 1.0000
9.500 1.1954 0.02409 0.01656 -0.0477 0.0280 1.0000
9.750 1.1977 0.02551 0.01803 -0.0449 0.0259 1.0000
10.000 1.2027 0.02681 0.01941 -0.0425 0.0247 1.0000
10.250 1.2085 0.02811 0.02078 -0.0404 0.0238 1.0000
10.500 1.2131 0.02958 0.02231 -0.0383 0.0230 1.0000
10.750 1.2152 0.03129 0.02409 -0.0362 0.0221 1.0000
11.000 1.2163 0.03317 0.02603 -0.0343 0.0214 1.0000
11.250 1.2118 0.03566 0.02860 -0.0322 0.0207 1.0000
11.500 1.2035 0.03863 0.03167 -0.0302 0.0202 1.0000
11.750 1.2072 0.04063 0.03375 -0.0290 0.0198 1.0000
12.000 1.2100 0.04279 0.03598 -0.0279 0.0194 1.0000
12.250 1.2118 0.04509 0.03835 -0.0269 0.0187 1.0000
12.500 1.2106 0.04777 0.04111 -0.0259 0.0184 1.0000
12.750 1.2081 0.05064 0.04405 -0.0250 0.0183 1.0000
13.000 1.2102 0.05307 0.04654 -0.0244 0.0176 1.0000
13.250 1.2085 0.05591 0.04943 -0.0236 0.0172 1.0000
13.500 1.2064 0.05884 0.05241 -0.0230 0.0169 1.0000
13.750 1.2038 0.06181 0.05543 -0.0223 0.0166 1.0000
14.000 1.2013 0.06471 0.05838 -0.0215 0.0164 1.0000
14.250 1.1983 0.06736 0.06105 -0.0201 0.0160 1.0000
14.500 1.2036 0.06954 0.06330 -0.0197 0.0158 1.0000
14.750 1.2089 0.07159 0.06540 -0.0190 0.0157 1.0000
15.000 1.2144 0.07374 0.06762 -0.0185 0.0153 1.0000
15.250 1.2193 0.07603 0.06999 -0.0183 0.0147 1.0000
15.500 1.2265 0.07771 0.07171 -0.0174 0.0146 1.0000
15.750 1.2315 0.07997 0.07402 -0.0172 0.0142 1.0000
16.000 1.2386 0.08176 0.07586 -0.0166 0.0139 1.0000
16.250 1.2451 0.08371 0.07784 -0.0161 0.0136 1.0000
16.500 1.2526 0.08545 0.07961 -0.0155 0.0134 1.0000
16.750 1.2613 0.08691 0.08109 -0.0147 0.0131 1.0000
17.000 1.2905 0.08475 0.07886 -0.0107 0.0126 1.0000
17.250 1.2951 0.08707 0.08130 -0.0104 0.0125 1.0000
17.500 1.2962 0.08995 0.08432 -0.0104 0.0124 1.0000
17.750 1.2953 0.09316 0.08769 -0.0107 0.0122 1.0000
18.000 1.2990 0.09563 0.09028 -0.0104 0.0122 1.0000
18.250 1.2989 0.09871 0.09352 -0.0104 0.0120 1.0000
18.500 1.2993 0.10174 0.09670 -0.0104 0.0120 1.0000
18.750 1.2944 0.10567 0.10081 -0.0110 0.0118 1.0000
19.000 1.2909 0.10938 0.10467 -0.0115 0.0119 1.0000
19.250 1.2823 0.11400 0.10947 -0.0127 0.0117 1.0000
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