BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Reynolds number: 200,000 Max Cl/Cd: 53.67 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v13009-il-200000-n5.txt Download as CSV file: xf-v13009-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V(1.95)3009-1.25 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6949 0.06536 0.06154 -0.0207 1.0000 0.0222
-9.000 -0.7124 0.05723 0.05318 -0.0237 1.0000 0.0221
-8.750 -0.7323 0.04760 0.04310 -0.0249 1.0000 0.0221
-8.500 -0.7430 0.03966 0.03450 -0.0243 1.0000 0.0224
-8.250 -0.7288 0.03771 0.03240 -0.0236 1.0000 0.0228
-8.000 -0.7127 0.03591 0.03043 -0.0229 1.0000 0.0232
-7.750 -0.6978 0.03344 0.02769 -0.0220 1.0000 0.0237
-7.500 -0.6832 0.03046 0.02432 -0.0208 1.0000 0.0241
-7.250 -0.6666 0.02780 0.02126 -0.0196 1.0000 0.0244
-7.000 -0.6477 0.02561 0.01874 -0.0184 1.0000 0.0249
-6.750 -0.6273 0.02376 0.01657 -0.0173 1.0000 0.0255
-6.500 -0.6059 0.02217 0.01470 -0.0163 1.0000 0.0261
-6.250 -0.5837 0.02081 0.01311 -0.0153 1.0000 0.0267
-6.000 -0.5611 0.01966 0.01176 -0.0142 1.0000 0.0274
-5.750 -0.5387 0.01873 0.01079 -0.0133 1.0000 0.0284
-5.500 -0.5157 0.01817 0.01021 -0.0125 1.0000 0.0296
-5.250 -0.4928 0.01754 0.00953 -0.0115 1.0000 0.0309
-5.000 -0.4700 0.01679 0.00872 -0.0105 1.0000 0.0323
-4.750 -0.4472 0.01608 0.00791 -0.0094 1.0000 0.0337
-4.500 -0.4249 0.01541 0.00726 -0.0084 1.0000 0.0353
-4.250 -0.4021 0.01495 0.00681 -0.0074 1.0000 0.0374
-4.000 -0.3794 0.01450 0.00633 -0.0064 1.0000 0.0403
-3.750 -0.3570 0.01408 0.00594 -0.0054 1.0000 0.0440
-3.500 -0.3254 0.01375 0.00561 -0.0063 0.9962 0.0496
-3.250 -0.2894 0.01330 0.00520 -0.0081 0.9896 0.0556
-3.000 -0.2525 0.01299 0.00487 -0.0101 0.9828 0.0631
-2.750 -0.2160 0.01264 0.00456 -0.0120 0.9737 0.0722
-2.500 -0.1801 0.01225 0.00422 -0.0137 0.9610 0.0815
-2.250 -0.1447 0.01192 0.00390 -0.0151 0.9465 0.0915
-2.000 -0.1111 0.01159 0.00362 -0.0162 0.9315 0.1051
-1.750 -0.0786 0.01123 0.00337 -0.0170 0.9114 0.1305
-1.250 -0.0269 0.00938 0.00283 -0.0164 0.8563 0.4923
-1.000 -0.0065 0.00874 0.00281 -0.0142 0.8295 0.6659
-0.750 0.0159 0.00849 0.00281 -0.0122 0.8039 0.7637
-0.500 0.0405 0.00842 0.00280 -0.0106 0.7776 0.8222
-0.250 0.0683 0.00844 0.00281 -0.0097 0.7503 0.8695
0.000 0.1027 0.00855 0.00283 -0.0102 0.7180 0.9182
0.250 0.1434 0.00875 0.00286 -0.0120 0.6788 0.9585
0.500 0.1854 0.00892 0.00283 -0.0146 0.6403 0.9783
0.750 0.2220 0.00907 0.00277 -0.0163 0.6052 0.9872
1.000 0.2573 0.00922 0.00272 -0.0179 0.5698 0.9944
1.250 0.2924 0.00938 0.00268 -0.0195 0.5345 1.0000
1.500 0.3166 0.00954 0.00268 -0.0188 0.5021 1.0000
1.750 0.3407 0.00973 0.00269 -0.0181 0.4675 1.0000
2.250 0.3887 0.01019 0.00279 -0.0166 0.3969 1.0000
2.500 0.4127 0.01044 0.00288 -0.0159 0.3667 1.0000
2.750 0.4368 0.01070 0.00299 -0.0152 0.3391 1.0000
3.000 0.4610 0.01096 0.00313 -0.0145 0.3118 1.0000
3.250 0.4849 0.01127 0.00328 -0.0138 0.2836 1.0000
3.500 0.5088 0.01159 0.00346 -0.0131 0.2583 1.0000
3.750 0.5329 0.01188 0.00365 -0.0124 0.2373 1.0000
4.000 0.5573 0.01217 0.00386 -0.0118 0.2216 1.0000
4.250 0.5817 0.01246 0.00409 -0.0111 0.2094 1.0000
4.500 0.6062 0.01276 0.00433 -0.0105 0.1992 1.0000
4.750 0.6308 0.01306 0.00459 -0.0099 0.1899 1.0000
5.000 0.6555 0.01336 0.00489 -0.0093 0.1824 1.0000
5.250 0.6800 0.01369 0.00519 -0.0087 0.1748 1.0000
5.500 0.7048 0.01401 0.00551 -0.0082 0.1676 1.0000
5.750 0.7295 0.01434 0.00584 -0.0076 0.1600 1.0000
6.000 0.7542 0.01469 0.00620 -0.0071 0.1528 1.0000
6.250 0.7790 0.01501 0.00654 -0.0066 0.1442 1.0000
6.500 0.8039 0.01533 0.00689 -0.0061 0.1358 1.0000
6.750 0.8285 0.01569 0.00723 -0.0056 0.1269 1.0000
7.000 0.8536 0.01600 0.00761 -0.0052 0.1173 1.0000
7.250 0.8781 0.01637 0.00800 -0.0047 0.1081 1.0000
7.500 0.9022 0.01681 0.00841 -0.0041 0.0995 1.0000
7.750 0.9261 0.01728 0.00891 -0.0036 0.0921 1.0000
8.000 0.9494 0.01783 0.00947 -0.0030 0.0864 1.0000
8.250 0.9726 0.01839 0.01007 -0.0024 0.0808 1.0000
8.500 0.9947 0.01907 0.01075 -0.0017 0.0760 1.0000
8.750 1.0179 0.01964 0.01145 -0.0011 0.0716 1.0000
9.000 1.0399 0.02031 0.01216 -0.0004 0.0676 1.0000
9.250 1.0607 0.02113 0.01300 0.0004 0.0644 1.0000
9.500 1.0826 0.02181 0.01382 0.0011 0.0617 1.0000
9.750 1.1038 0.02255 0.01468 0.0019 0.0590 1.0000
10.000 1.1238 0.02337 0.01555 0.0027 0.0566 1.0000
10.250 1.1423 0.02437 0.01658 0.0037 0.0544 1.0000
10.500 1.1623 0.02520 0.01757 0.0046 0.0525 1.0000
10.750 1.1811 0.02612 0.01863 0.0055 0.0507 1.0000
11.000 1.1991 0.02706 0.01970 0.0065 0.0490 1.0000
11.250 1.2161 0.02799 0.02071 0.0074 0.0471 1.0000
11.500 1.2304 0.02919 0.02194 0.0086 0.0451 1.0000
11.750 1.2471 0.03007 0.02304 0.0096 0.0430 1.0000
12.000 1.2621 0.03101 0.02412 0.0107 0.0408 1.0000
12.250 1.2750 0.03201 0.02524 0.0118 0.0389 1.0000
12.500 1.2819 0.03331 0.02660 0.0136 0.0376 1.0000
12.750 1.2875 0.03482 0.02825 0.0152 0.0364 1.0000
13.000 1.2939 0.03636 0.03000 0.0165 0.0351 1.0000
13.250 1.2982 0.03814 0.03195 0.0174 0.0338 1.0000
13.500 1.3010 0.04019 0.03416 0.0178 0.0326 1.0000
13.750 1.3018 0.04263 0.03674 0.0177 0.0316 1.0000
14.000 1.2997 0.04563 0.03987 0.0169 0.0307 1.0000
14.250 1.2940 0.04937 0.04372 0.0155 0.0300 1.0000
14.500 1.2872 0.05362 0.04817 0.0134 0.0294 1.0000
14.750 1.2785 0.05850 0.05328 0.0108 0.0287 1.0000
15.000 1.2662 0.06418 0.05917 0.0075 0.0281 1.0000
15.250 1.2504 0.07066 0.06584 0.0037 0.0277 1.0000
15.500 1.2309 0.07795 0.07331 -0.0006 0.0274 1.0000
15.750 1.2080 0.08600 0.08153 -0.0052 0.0273 1.0000
16.000 1.1815 0.09482 0.09050 -0.0102 0.0272 1.0000
16.250 1.1518 0.10460 0.10043 -0.0156 0.0273 1.0000
16.500 1.1166 0.11591 0.11191 -0.0219 0.0275 1.0000
16.750 1.0650 0.13161 0.12779 -0.0306 0.0280 1.0000
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Polar data table (+)
Polar graphs
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