B-29 TIP AIRFOIL (b29tip-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: B-29 TIP AIRFOIL (b29tip-il) Reynolds number: 500,000 Max Cl/Cd: 84.27 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b29tip-il-500000-n5.txt Download as CSV file: xf-b29tip-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5371 0.08430 0.08215 -0.0080 1.0000 0.0120
-8.750 -0.5423 0.07965 0.07753 -0.0110 1.0000 0.0119
-8.500 -0.5541 0.07448 0.07240 -0.0151 1.0000 0.0121
-8.250 -0.5640 0.06925 0.06716 -0.0180 1.0000 0.0122
-8.000 -0.5684 0.06354 0.06139 -0.0208 0.9820 0.0122
-7.750 -0.5589 0.05491 0.05244 -0.0276 0.8939 0.0122
-7.500 -0.5609 0.04884 0.04605 -0.0274 0.8592 0.0123
-7.250 -0.5609 0.04224 0.03908 -0.0265 0.8371 0.0124
-7.000 -0.5602 0.03495 0.03127 -0.0245 0.8201 0.0125
-6.750 -0.5553 0.02892 0.02465 -0.0221 0.8055 0.0126
-6.500 -0.5413 0.02558 0.02082 -0.0203 0.7917 0.0128
-6.250 -0.5223 0.02358 0.01844 -0.0190 0.7789 0.0130
-6.000 -0.5031 0.02147 0.01593 -0.0177 0.7669 0.0131
-5.750 -0.4818 0.01975 0.01387 -0.0166 0.7563 0.0131
-5.500 -0.4591 0.01837 0.01220 -0.0157 0.7460 0.0132
-5.250 -0.4352 0.01727 0.01084 -0.0150 0.7356 0.0133
-5.000 -0.4109 0.01619 0.00955 -0.0143 0.7258 0.0134
-4.750 -0.3877 0.01461 0.00771 -0.0134 0.7169 0.0138
-4.500 -0.3629 0.01377 0.00673 -0.0128 0.7077 0.0142
-4.250 -0.3377 0.01316 0.00602 -0.0123 0.6987 0.0146
-4.000 -0.3123 0.01267 0.00544 -0.0118 0.6901 0.0150
-3.750 -0.2866 0.01221 0.00490 -0.0113 0.6813 0.0153
-3.500 -0.2609 0.01180 0.00440 -0.0109 0.6730 0.0157
-3.250 -0.2351 0.01144 0.00397 -0.0104 0.6644 0.0162
-3.000 -0.2091 0.01112 0.00358 -0.0100 0.6565 0.0168
-2.750 -0.1829 0.01087 0.00326 -0.0096 0.6483 0.0177
-2.500 -0.1566 0.01060 0.00293 -0.0093 0.6403 0.0183
-2.000 -0.1039 0.01010 0.00229 -0.0085 0.6246 0.0202
-1.750 -0.0775 0.00990 0.00204 -0.0081 0.6172 0.0228
-1.500 -0.0507 0.00974 0.00185 -0.0078 0.6095 0.0276
-1.250 -0.0246 0.00952 0.00171 -0.0075 0.6023 0.0503
-1.000 0.0019 0.00933 0.00160 -0.0072 0.5947 0.0778
-0.750 0.0276 0.00908 0.00149 -0.0069 0.5880 0.1282
-0.500 0.0514 0.00857 0.00140 -0.0063 0.5809 0.2582
0.000 0.0911 0.00638 0.00141 -0.0030 0.5683 0.9022
0.250 0.1379 0.00651 0.00149 -0.0068 0.5610 0.9379
0.500 0.1808 0.00667 0.00161 -0.0098 0.5541 0.9586
0.750 0.2293 0.00694 0.00179 -0.0140 0.5471 0.9759
1.000 0.2723 0.00704 0.00184 -0.0172 0.5405 0.9810
1.250 0.3085 0.00713 0.00188 -0.0190 0.5339 0.9860
1.500 0.3444 0.00717 0.00187 -0.0208 0.5281 0.9883
1.750 0.3759 0.00720 0.00187 -0.0217 0.5217 0.9900
2.000 0.4066 0.00725 0.00189 -0.0224 0.5159 0.9919
2.250 0.4370 0.00728 0.00192 -0.0230 0.5100 0.9936
2.500 0.4678 0.00733 0.00195 -0.0237 0.5040 0.9951
2.750 0.4992 0.00735 0.00198 -0.0246 0.4978 0.9964
3.000 0.5303 0.00739 0.00203 -0.0254 0.4916 0.9979
3.250 0.5613 0.00744 0.00207 -0.0262 0.4815 0.9993
3.500 0.5897 0.00753 0.00211 -0.0265 0.4626 1.0000
3.750 0.6141 0.00764 0.00218 -0.0259 0.4435 1.0000
4.000 0.6386 0.00777 0.00225 -0.0253 0.4212 1.0000
4.250 0.6630 0.00791 0.00235 -0.0247 0.4026 1.0000
4.500 0.6868 0.00815 0.00248 -0.0240 0.3708 1.0000
4.750 0.7097 0.00851 0.00269 -0.0233 0.3261 1.0000
5.000 0.7310 0.00910 0.00300 -0.0225 0.2603 1.0000
5.250 0.7483 0.01029 0.00362 -0.0213 0.1440 1.0000
5.500 0.7684 0.01102 0.00409 -0.0203 0.0920 1.0000
5.750 0.7898 0.01151 0.00447 -0.0194 0.0653 1.0000
6.000 0.8117 0.01192 0.00485 -0.0185 0.0501 1.0000
6.250 0.8326 0.01243 0.00527 -0.0175 0.0318 1.0000
6.500 0.8530 0.01299 0.00575 -0.0164 0.0179 1.0000
6.750 0.8743 0.01343 0.00621 -0.0153 0.0145 1.0000
7.000 0.8949 0.01392 0.00672 -0.0142 0.0125 1.0000
7.250 0.9150 0.01446 0.00733 -0.0130 0.0114 1.0000
7.500 0.9353 0.01495 0.00789 -0.0118 0.0107 1.0000
7.750 0.9551 0.01547 0.00847 -0.0106 0.0100 1.0000
8.000 0.9743 0.01602 0.00908 -0.0094 0.0092 1.0000
8.250 0.9924 0.01666 0.00977 -0.0080 0.0086 1.0000
8.500 1.0082 0.01748 0.01068 -0.0063 0.0081 1.0000
8.750 1.0215 0.01849 0.01177 -0.0043 0.0077 1.0000
9.000 1.0379 0.01917 0.01254 -0.0027 0.0075 1.0000
9.250 1.0521 0.02001 0.01345 -0.0009 0.0073 1.0000
9.500 1.0655 0.02087 0.01441 0.0010 0.0071 1.0000
9.750 1.0775 0.02179 0.01542 0.0030 0.0069 1.0000
10.000 1.0878 0.02280 0.01652 0.0053 0.0066 1.0000
10.250 1.0957 0.02384 0.01766 0.0078 0.0065 1.0000
10.500 1.1005 0.02486 0.01878 0.0107 0.0063 1.0000
10.750 1.1054 0.02603 0.02005 0.0132 0.0062 1.0000
11.000 1.1132 0.02712 0.02122 0.0148 0.0059 1.0000
11.250 1.1211 0.02831 0.02248 0.0162 0.0057 1.0000
11.500 1.1259 0.02996 0.02424 0.0176 0.0056 1.0000
11.750 1.1303 0.03177 0.02617 0.0187 0.0055 1.0000
12.000 1.1357 0.03346 0.02793 0.0194 0.0053 1.0000
12.250 1.1349 0.03601 0.03061 0.0204 0.0051 1.0000
12.500 1.1322 0.03889 0.03366 0.0213 0.0050 1.0000
12.750 1.1353 0.04110 0.03603 0.0216 0.0049 1.0000
13.000 1.1347 0.04384 0.03893 0.0218 0.0049 1.0000
13.250 1.1325 0.04683 0.04208 0.0217 0.0049 1.0000
13.500 1.1279 0.05023 0.04568 0.0214 0.0049 1.0000
13.750 1.1255 0.05341 0.04902 0.0208 0.0048 1.0000
14.000 1.1181 0.05737 0.05314 0.0198 0.0048 1.0000
14.250 1.1092 0.06168 0.05764 0.0185 0.0047 1.0000
14.500 1.0984 0.06645 0.06257 0.0168 0.0047 1.0000
14.750 1.0893 0.07123 0.06752 0.0148 0.0046 1.0000
15.000 1.0750 0.07712 0.07358 0.0122 0.0047 1.0000
15.250 1.0579 0.08383 0.08045 0.0089 0.0047 1.0000
15.500 1.0436 0.09048 0.08725 0.0055 0.0047 1.0000
15.750 1.0264 0.09808 0.09500 0.0014 0.0047 1.0000
16.000 1.0034 0.10737 0.10445 -0.0036 0.0047 1.0000
16.250 0.9840 0.11649 0.11372 -0.0086 0.0047 1.0000
16.500 0.9622 0.12686 0.12420 -0.0142 0.0047 1.0000
16.750 0.9323 0.13998 0.13744 -0.0209 0.0049 1.0000
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