B-29 TIP AIRFOIL (b29tip-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: B-29 TIP AIRFOIL (b29tip-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.95 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b29tip-il-1000000-n5.txt Download as CSV file: xf-b29tip-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: B-29 TIP 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5632 0.08138 0.07985 -0.0092 1.0000 0.0082
-9.000 -0.5693 0.07413 0.07260 -0.0173 0.9455 0.0083
-8.750 -0.5862 0.06830 0.06643 -0.0216 0.8506 0.0083
-8.500 -0.6028 0.06144 0.05940 -0.0240 0.8217 0.0085
-8.000 -0.6799 0.02848 0.02504 -0.0221 0.7921 0.0093
-7.500 -0.6546 0.02265 0.01838 -0.0188 0.7658 0.0094
-7.250 -0.6396 0.01998 0.01529 -0.0171 0.7541 0.0095
-7.000 -0.6206 0.01808 0.01307 -0.0159 0.7437 0.0096
-6.750 -0.5990 0.01680 0.01156 -0.0150 0.7337 0.0098
-6.500 -0.5757 0.01583 0.01042 -0.0143 0.7240 0.0100
-6.250 -0.5520 0.01491 0.00932 -0.0136 0.7146 0.0100
-5.750 -0.5029 0.01347 0.00759 -0.0124 0.6965 0.0103
-5.500 -0.4777 0.01289 0.00691 -0.0120 0.6882 0.0105
-5.250 -0.4522 0.01239 0.00630 -0.0115 0.6793 0.0107
-5.000 -0.4267 0.01189 0.00571 -0.0110 0.6711 0.0108
-4.750 -0.4009 0.01150 0.00523 -0.0106 0.6626 0.0111
-4.500 -0.3750 0.01110 0.00475 -0.0102 0.6546 0.0114
-4.250 -0.3490 0.01075 0.00432 -0.0098 0.6464 0.0117
-4.000 -0.3229 0.01043 0.00393 -0.0094 0.6383 0.0121
-3.750 -0.2967 0.01012 0.00355 -0.0091 0.6306 0.0123
-3.500 -0.2704 0.00985 0.00322 -0.0087 0.6225 0.0125
-3.250 -0.2439 0.00962 0.00293 -0.0084 0.6149 0.0128
-3.000 -0.2173 0.00939 0.00264 -0.0081 0.6071 0.0130
-2.750 -0.1906 0.00921 0.00241 -0.0078 0.5997 0.0132
-2.500 -0.1638 0.00902 0.00217 -0.0076 0.5921 0.0133
-2.250 -0.1372 0.00881 0.00190 -0.0072 0.5851 0.0139
-2.000 -0.1105 0.00862 0.00167 -0.0070 0.5775 0.0151
-1.750 -0.0835 0.00849 0.00151 -0.0067 0.5709 0.0162
-1.500 -0.0563 0.00838 0.00137 -0.0066 0.5638 0.0176
-1.250 -0.0291 0.00828 0.00125 -0.0064 0.5573 0.0207
-1.000 -0.0023 0.00814 0.00115 -0.0061 0.5506 0.0341
-0.750 0.0244 0.00800 0.00107 -0.0059 0.5445 0.0579
-0.500 0.0515 0.00788 0.00101 -0.0058 0.5382 0.0783
-0.250 0.0779 0.00772 0.00096 -0.0055 0.5323 0.1197
0.000 0.1024 0.00730 0.00090 -0.0050 0.5271 0.2414
0.250 0.1264 0.00687 0.00086 -0.0044 0.5214 0.3737
0.500 0.1353 0.00549 0.00077 -0.0007 0.5165 0.7714
0.750 0.1580 0.00514 0.00084 0.0007 0.5118 0.8948
1.000 0.1967 0.00518 0.00093 -0.0015 0.5057 0.9392
1.250 0.2399 0.00533 0.00108 -0.0046 0.4998 0.9653
1.500 0.2768 0.00547 0.00118 -0.0065 0.4943 0.9738
1.750 0.3125 0.00556 0.00124 -0.0082 0.4888 0.9766
2.000 0.3499 0.00565 0.00130 -0.0103 0.4832 0.9791
2.250 0.3830 0.00572 0.00135 -0.0115 0.4772 0.9815
2.500 0.4123 0.00578 0.00140 -0.0118 0.4721 0.9834
2.750 0.4402 0.00584 0.00145 -0.0118 0.4656 0.9854
3.000 0.4718 0.00592 0.00148 -0.0127 0.4518 0.9861
3.250 0.5026 0.00606 0.00153 -0.0135 0.4300 0.9870
3.500 0.5332 0.00619 0.00159 -0.0143 0.4077 0.9879
3.750 0.5634 0.00635 0.00167 -0.0149 0.3846 0.9890
4.000 0.5928 0.00659 0.00179 -0.0155 0.3523 0.9902
4.250 0.6210 0.00695 0.00196 -0.0159 0.3061 0.9915
4.500 0.6480 0.00748 0.00222 -0.0162 0.2423 0.9930
4.750 0.6729 0.00828 0.00263 -0.0162 0.1549 0.9945
5.000 0.7012 0.00886 0.00297 -0.0169 0.1017 0.9953
5.250 0.7299 0.00932 0.00327 -0.0175 0.0662 0.9963
5.500 0.7592 0.00965 0.00352 -0.0182 0.0494 0.9973
5.750 0.7878 0.01005 0.00382 -0.0188 0.0307 0.9983
6.000 0.8161 0.01049 0.00418 -0.0193 0.0157 0.9992
6.250 0.8450 0.01083 0.00451 -0.0198 0.0114 0.9999
6.500 0.8685 0.01112 0.00481 -0.0192 0.0102 1.0000
6.750 0.8907 0.01144 0.00515 -0.0182 0.0092 1.0000
7.000 0.9122 0.01184 0.00559 -0.0172 0.0080 1.0000
7.250 0.9340 0.01218 0.00597 -0.0163 0.0076 1.0000
7.500 0.9557 0.01252 0.00634 -0.0153 0.0072 1.0000
7.750 0.9770 0.01289 0.00675 -0.0143 0.0069 1.0000
8.000 0.9978 0.01330 0.00720 -0.0132 0.0065 1.0000
8.250 1.0182 0.01373 0.00769 -0.0120 0.0062 1.0000
8.500 1.0383 0.01418 0.00817 -0.0109 0.0059 1.0000
8.750 1.0574 0.01470 0.00873 -0.0096 0.0056 1.0000
9.000 1.0744 0.01540 0.00950 -0.0080 0.0052 1.0000
9.250 1.0898 0.01621 0.01038 -0.0062 0.0050 1.0000
9.500 1.1081 0.01673 0.01096 -0.0049 0.0049 1.0000
9.750 1.1259 0.01726 0.01154 -0.0035 0.0048 1.0000
10.000 1.1440 0.01775 0.01210 -0.0021 0.0046 1.0000
10.250 1.1594 0.01842 0.01284 -0.0005 0.0044 1.0000
10.500 1.1745 0.01909 0.01357 0.0012 0.0043 1.0000
10.750 1.1877 0.01986 0.01441 0.0031 0.0042 1.0000
11.000 1.2005 0.02060 0.01521 0.0049 0.0040 1.0000
11.250 1.2109 0.02136 0.01604 0.0072 0.0039 1.0000
11.500 1.2148 0.02226 0.01702 0.0103 0.0038 1.0000
11.750 1.2193 0.02334 0.01818 0.0128 0.0038 1.0000
12.000 1.2276 0.02437 0.01928 0.0143 0.0037 1.0000
12.250 1.2362 0.02552 0.02052 0.0156 0.0036 1.0000
12.500 1.2416 0.02707 0.02216 0.0167 0.0035 1.0000
12.750 1.2494 0.02850 0.02366 0.0175 0.0034 1.0000
13.000 1.2533 0.03040 0.02567 0.0182 0.0034 1.0000
13.250 1.2558 0.03253 0.02791 0.0187 0.0034 1.0000
13.500 1.2562 0.03497 0.03047 0.0191 0.0033 1.0000
13.750 1.2580 0.03734 0.03294 0.0191 0.0032 1.0000
14.000 1.2569 0.04008 0.03579 0.0191 0.0032 1.0000
14.250 1.2486 0.04376 0.03963 0.0189 0.0031 1.0000
14.500 1.2373 0.04790 0.04394 0.0184 0.0031 1.0000
14.750 1.2428 0.05015 0.04626 0.0178 0.0030 1.0000
15.000 1.2341 0.05419 0.05044 0.0169 0.0030 1.0000
15.250 1.2191 0.05920 0.05562 0.0156 0.0031 1.0000
15.500 1.2190 0.06246 0.05897 0.0144 0.0030 1.0000
15.750 1.2129 0.06670 0.06333 0.0128 0.0030 1.0000
16.000 1.2000 0.07214 0.06891 0.0107 0.0030 1.0000
16.250 1.1945 0.07663 0.07350 0.0087 0.0030 1.0000
16.500 1.1860 0.08176 0.07876 0.0064 0.0029 1.0000
16.750 1.1638 0.08936 0.08650 0.0030 0.0030 1.0000
17.000 1.1520 0.09545 0.09271 0.0000 0.0030 1.0000
17.250 1.1361 0.10254 0.09992 -0.0034 0.0029 1.0000
17.500 1.1060 0.11261 0.11015 -0.0083 0.0030 1.0000
17.750 1.0809 0.12231 0.11999 -0.0132 0.0030 1.0000
18.000 1.0548 0.13262 0.13043 -0.0183 0.0030 1.0000
18.250 1.0239 0.14479 0.14274 -0.0244 0.0031 1.0000
18.500 1.0047 0.15460 0.15264 -0.0292 0.0030 1.0000
18.750 0.9727 0.16833 0.16649 -0.0360 0.0031 1.0000
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