B-29 TIP AIRFOIL (b29tip-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: B-29 TIP AIRFOIL (b29tip-il) Reynolds number: 500,000 Max Cl/Cd: 91.38 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b29tip-il-500000.txt Download as CSV file: xf-b29tip-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5157 0.08702 0.08489 -0.0068 1.0000 0.0218
-8.500 -0.5193 0.08247 0.08037 -0.0103 1.0000 0.0226
-8.250 -0.5292 0.07738 0.07532 -0.0155 1.0000 0.0232
-7.000 -0.5348 0.04979 0.04721 -0.0244 1.0000 0.0247
-6.750 -0.5226 0.04759 0.04498 -0.0241 1.0000 0.0253
-6.500 -0.5023 0.04486 0.04216 -0.0255 0.9677 0.0260
-6.250 -0.4740 0.04135 0.03841 -0.0283 0.9206 0.0271
-6.000 -0.4603 0.03850 0.03524 -0.0270 0.8860 0.0286
-5.750 -0.4378 0.03736 0.03361 -0.0248 0.8622 0.0320
-5.500 -0.4359 0.03076 0.02641 -0.0222 0.8439 0.0332
-5.250 -0.4180 0.02858 0.02412 -0.0213 0.8280 0.0343
-5.000 -0.3978 0.02711 0.02249 -0.0204 0.8135 0.0354
-4.750 -0.3767 0.02558 0.02074 -0.0194 0.8000 0.0372
-4.500 -0.3542 0.02411 0.01898 -0.0182 0.7877 0.0398
-4.250 -0.3333 0.01734 0.01105 -0.0143 0.7784 0.0243
-4.000 -0.3074 0.01675 0.01030 -0.0136 0.7674 0.0239
-3.750 -0.2825 0.01484 0.00816 -0.0129 0.7567 0.0236
-3.500 -0.2566 0.01397 0.00714 -0.0123 0.7464 0.0238
-3.250 -0.2320 0.01264 0.00565 -0.0115 0.7370 0.0243
-3.000 -0.2077 0.01171 0.00461 -0.0106 0.7272 0.0251
-2.750 -0.1829 0.01112 0.00396 -0.0099 0.7175 0.0262
-2.500 -0.1573 0.01077 0.00355 -0.0094 0.7086 0.0278
-2.250 -0.1314 0.01047 0.00320 -0.0089 0.6991 0.0298
-2.000 -0.1053 0.01018 0.00283 -0.0084 0.6903 0.0318
-1.750 -0.0799 0.00979 0.00238 -0.0077 0.6819 0.0380
-1.500 -0.0547 0.00935 0.00210 -0.0071 0.6730 0.0802
-1.250 -0.0305 0.00890 0.00193 -0.0065 0.6653 0.1679
-1.000 -0.0098 0.00806 0.00179 -0.0054 0.6568 0.3752
-0.750 -0.0022 0.00658 0.00164 -0.0014 0.6499 0.7451
-0.500 0.0620 0.00651 0.00206 -0.0081 0.6410 0.9512
-0.250 0.1105 0.00685 0.00228 -0.0120 0.6329 0.9705
0.000 0.1643 0.00705 0.00235 -0.0174 0.6244 0.9781
0.250 0.2319 0.00723 0.00243 -0.0258 0.6155 0.9910
0.500 0.2937 0.00717 0.00225 -0.0331 0.6074 1.0000
0.750 0.3180 0.00715 0.00221 -0.0325 0.5999 1.0000
1.000 0.3422 0.00718 0.00217 -0.0318 0.5935 1.0000
1.250 0.3667 0.00717 0.00215 -0.0312 0.5860 1.0000
1.750 0.4157 0.00722 0.00213 -0.0300 0.5730 1.0000
2.000 0.4403 0.00726 0.00214 -0.0294 0.5665 1.0000
2.250 0.4651 0.00729 0.00217 -0.0288 0.5599 1.0000
2.500 0.4898 0.00734 0.00220 -0.0283 0.5536 1.0000
2.750 0.5146 0.00739 0.00226 -0.0277 0.5472 1.0000
3.000 0.5395 0.00743 0.00230 -0.0271 0.5398 1.0000
3.250 0.5642 0.00747 0.00234 -0.0265 0.5304 1.0000
3.500 0.5888 0.00752 0.00237 -0.0259 0.5183 1.0000
3.750 0.6133 0.00756 0.00241 -0.0253 0.5039 1.0000
4.000 0.6380 0.00762 0.00246 -0.0246 0.4899 1.0000
4.250 0.6627 0.00770 0.00255 -0.0241 0.4799 1.0000
4.500 0.6875 0.00778 0.00264 -0.0235 0.4665 1.0000
4.750 0.7119 0.00788 0.00274 -0.0228 0.4457 1.0000
5.000 0.7356 0.00805 0.00284 -0.0221 0.4128 1.0000
5.250 0.7589 0.00832 0.00299 -0.0214 0.3752 1.0000
5.500 0.7808 0.00879 0.00324 -0.0205 0.3204 1.0000
5.750 0.7983 0.00987 0.00379 -0.0193 0.2065 1.0000
6.000 0.8148 0.01108 0.00453 -0.0180 0.1126 1.0000
6.250 0.8332 0.01196 0.00513 -0.0167 0.0612 1.0000
6.500 0.8511 0.01290 0.00587 -0.0152 0.0278 1.0000
6.750 0.8701 0.01365 0.00664 -0.0138 0.0218 1.0000
7.000 0.8904 0.01421 0.00727 -0.0126 0.0199 1.0000
7.250 0.9097 0.01483 0.00796 -0.0112 0.0182 1.0000
7.500 0.9246 0.01587 0.00907 -0.0093 0.0164 1.0000
7.750 0.9412 0.01670 0.00997 -0.0076 0.0157 1.0000
8.000 0.9578 0.01749 0.01084 -0.0059 0.0151 1.0000
8.250 0.9732 0.01837 0.01180 -0.0040 0.0146 1.0000
8.500 0.9879 0.01931 0.01282 -0.0021 0.0140 1.0000
8.750 1.0018 0.02032 0.01392 -0.0001 0.0138 1.0000
9.000 1.0155 0.02138 0.01504 0.0019 0.0132 1.0000
9.250 1.0287 0.02253 0.01626 0.0038 0.0129 1.0000
9.500 1.0416 0.02387 0.01768 0.0058 0.0127 1.0000
9.750 1.0546 0.02533 0.01923 0.0077 0.0124 1.0000
10.000 1.0669 0.02773 0.02174 0.0094 0.0119 1.0000
10.250 1.0774 0.03068 0.02495 0.0112 0.0116 1.0000
10.500 1.0872 0.03226 0.02672 0.0132 0.0115 1.0000
10.750 1.0942 0.03427 0.02895 0.0153 0.0114 1.0000
11.000 1.0960 0.03675 0.03164 0.0180 0.0114 1.0000
11.250 1.0967 0.04075 0.03587 0.0201 0.0117 1.0000
11.500 1.0917 0.04287 0.03817 0.0230 0.0117 1.0000
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Polar data table (+)
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