BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING VERTOL V43012-1.58 AIRFOIL (v43012-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.91 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v43012-il-1000000.txt Download as CSV file: xf-v43012-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V43012-1.58 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4181 0.08674 0.08509 -0.0255 1.0000 0.0158
-9.500 -0.4181 0.08330 0.08167 -0.0271 1.0000 0.0160
-9.250 -0.4210 0.07945 0.07784 -0.0293 1.0000 0.0162
-9.000 -0.4387 0.07353 0.07193 -0.0350 1.0000 0.0161
-8.750 -0.4587 0.07045 0.06884 -0.0342 1.0000 0.0163
-8.500 -0.4796 0.06786 0.06622 -0.0309 1.0000 0.0163
-8.250 -0.4917 0.06544 0.06377 -0.0282 1.0000 0.0165
-8.000 -0.4771 0.06079 0.05902 -0.0320 0.9971 0.0168
-7.750 -0.4609 0.05629 0.05438 -0.0351 0.9931 0.0175
-7.500 -0.4470 0.04873 0.04637 -0.0364 0.9866 0.0184
-7.250 -0.4339 0.04325 0.04070 -0.0379 0.9826 0.0187
-7.000 -0.4130 0.04120 0.03860 -0.0386 0.9768 0.0188
-6.750 -0.3844 0.03907 0.03639 -0.0406 0.9724 0.0191
-6.500 -0.3568 0.03688 0.03409 -0.0420 0.9639 0.0194
-6.250 -0.3260 0.03456 0.03164 -0.0438 0.9556 0.0203
-6.000 -0.3079 0.02883 0.02533 -0.0410 0.9385 0.0221
-5.750 -0.2826 0.02726 0.02364 -0.0414 0.9166 0.0223
-5.500 -0.2601 0.02614 0.02236 -0.0409 0.8812 0.0225
-5.250 -0.2408 0.02515 0.02113 -0.0393 0.8427 0.0228
-5.000 -0.2221 0.02419 0.01996 -0.0376 0.8047 0.0234
-4.250 -0.1642 0.01977 0.01468 -0.0314 0.7122 0.0267
-4.000 -0.1423 0.01913 0.01388 -0.0302 0.6830 0.0272
-3.750 -0.1204 0.01741 0.01172 -0.0280 0.6572 0.0304
-3.500 -0.0970 0.01672 0.01096 -0.0272 0.6330 0.0308
-3.250 -0.0731 0.01623 0.01037 -0.0264 0.6099 0.0314
-3.000 -0.0486 0.01586 0.00988 -0.0256 0.5878 0.0328
-2.750 -0.0242 0.01503 0.00885 -0.0246 0.5683 0.0360
-2.500 0.0043 0.01245 0.00598 -0.0236 0.5510 0.0290
-2.250 0.0287 0.01130 0.00468 -0.0225 0.5332 0.0272
-2.000 0.0529 0.01090 0.00418 -0.0215 0.5135 0.0272
-1.750 0.0771 0.01067 0.00387 -0.0206 0.4862 0.0277
-1.500 0.0995 0.01046 0.00347 -0.0193 0.4433 0.0278
-1.250 0.1222 0.01033 0.00319 -0.0181 0.4128 0.0279
-1.000 0.1459 0.01019 0.00296 -0.0171 0.3937 0.0283
-0.750 0.1702 0.01008 0.00276 -0.0161 0.3744 0.0286
-0.500 0.1946 0.01000 0.00259 -0.0153 0.3517 0.0289
-0.250 0.2190 0.00998 0.00245 -0.0144 0.3263 0.0293
0.000 0.2435 0.00999 0.00234 -0.0136 0.3015 0.0296
0.250 0.2685 0.01000 0.00226 -0.0129 0.2856 0.0298
0.500 0.2933 0.00994 0.00213 -0.0121 0.2741 0.0310
0.750 0.3187 0.00994 0.00208 -0.0115 0.2656 0.0320
1.000 0.3447 0.00994 0.00206 -0.0109 0.2592 0.0329
1.250 0.3708 0.00995 0.00205 -0.0104 0.2533 0.0346
1.500 0.3964 0.01001 0.00208 -0.0098 0.2460 0.0377
1.750 0.4228 0.00999 0.00212 -0.0094 0.2411 0.0573
2.000 0.4487 0.01001 0.00217 -0.0089 0.2348 0.0796
2.250 0.4625 0.00907 0.00215 -0.0064 0.2294 0.4769
2.500 0.4735 0.00824 0.00217 -0.0029 0.2268 0.7374
2.750 0.4889 0.00790 0.00228 0.0001 0.2232 0.8725
3.000 0.5216 0.00794 0.00246 -0.0006 0.2183 0.9341
3.250 0.5617 0.00815 0.00265 -0.0032 0.2128 0.9581
3.500 0.6012 0.00834 0.00282 -0.0055 0.2100 0.9710
3.750 0.6493 0.00859 0.00303 -0.0098 0.2060 0.9756
4.000 0.6886 0.00883 0.00321 -0.0121 0.2021 0.9807
4.250 0.7215 0.00905 0.00339 -0.0132 0.1981 0.9840
4.500 0.7580 0.00917 0.00350 -0.0151 0.1963 0.9853
4.750 0.7973 0.00932 0.00364 -0.0176 0.1937 0.9874
5.000 0.8354 0.00949 0.00378 -0.0199 0.1908 0.9900
5.250 0.8689 0.00967 0.00393 -0.0212 0.1878 0.9924
5.500 0.9017 0.00991 0.00414 -0.0224 0.1838 0.9944
5.750 0.9364 0.01000 0.00425 -0.0240 0.1820 0.9956
6.000 0.9702 0.01010 0.00435 -0.0254 0.1800 0.9970
6.250 1.0035 0.01021 0.00447 -0.0267 0.1773 0.9984
6.500 1.0363 0.01036 0.00461 -0.0280 0.1741 0.9997
6.750 1.0597 0.01057 0.00479 -0.0273 0.1704 1.0000
7.000 1.0795 0.01073 0.00497 -0.0258 0.1680 1.0000
7.250 1.1007 0.01082 0.00509 -0.0245 0.1660 1.0000
7.500 1.1213 0.01095 0.00522 -0.0232 0.1629 1.0000
7.750 1.1412 0.01112 0.00538 -0.0217 0.1593 1.0000
8.000 1.1599 0.01137 0.00561 -0.0200 0.1548 1.0000
8.250 1.1808 0.01149 0.00577 -0.0188 0.1523 1.0000
8.500 1.2010 0.01167 0.00595 -0.0174 0.1488 1.0000
8.750 1.2202 0.01191 0.00617 -0.0158 0.1446 1.0000
9.000 1.2392 0.01216 0.00643 -0.0142 0.1411 1.0000
9.250 1.2592 0.01236 0.00666 -0.0128 0.1387 1.0000
9.500 1.2787 0.01260 0.00689 -0.0114 0.1354 1.0000
9.750 1.2970 0.01292 0.00718 -0.0098 0.1311 1.0000
10.000 1.3162 0.01318 0.00747 -0.0083 0.1285 1.0000
10.250 1.3359 0.01342 0.00774 -0.0070 0.1265 1.0000
10.500 1.3549 0.01369 0.00804 -0.0055 0.1247 1.0000
10.750 1.3735 0.01399 0.00835 -0.0040 0.1228 1.0000
11.000 1.3912 0.01433 0.00871 -0.0024 0.1206 1.0000
11.250 1.4073 0.01475 0.00914 -0.0006 0.1181 1.0000
11.500 1.4258 0.01504 0.00947 0.0008 0.1168 1.0000
11.750 1.4446 0.01531 0.00980 0.0022 0.1157 1.0000
12.000 1.4621 0.01561 0.01015 0.0038 0.1142 1.0000
12.250 1.4768 0.01593 0.01050 0.0059 0.1123 1.0000
12.500 1.4901 0.01632 0.01091 0.0081 0.1101 1.0000
12.750 1.5010 0.01684 0.01144 0.0106 0.1071 1.0000
13.000 1.5157 0.01725 0.01190 0.0124 0.1055 1.0000
13.250 1.5329 0.01756 0.01228 0.0138 0.1043 1.0000
13.500 1.5493 0.01794 0.01272 0.0152 0.1026 1.0000
13.750 1.5641 0.01841 0.01322 0.0167 0.1001 1.0000
14.000 1.5768 0.01902 0.01386 0.0184 0.0977 1.0000
14.250 1.5865 0.01980 0.01468 0.0203 0.0949 1.0000
14.500 1.6048 0.02015 0.01511 0.0211 0.0931 1.0000
14.750 1.6195 0.02072 0.01573 0.0223 0.0898 1.0000
15.000 1.6295 0.02160 0.01661 0.0238 0.0857 1.0000
15.250 1.6415 0.02240 0.01745 0.0250 0.0798 1.0000
15.500 1.6433 0.02393 0.01891 0.0267 0.0678 1.0000
15.750 1.6317 0.02660 0.02149 0.0288 0.0542 1.0000
16.000 1.6258 0.02907 0.02399 0.0299 0.0487 1.0000
16.250 1.6185 0.03193 0.02691 0.0305 0.0447 1.0000
16.500 1.6124 0.03490 0.02996 0.0306 0.0415 1.0000
16.750 1.6057 0.03818 0.03333 0.0302 0.0398 1.0000
17.250 1.5848 0.04616 0.04153 0.0282 0.0366 1.0000
17.500 1.5699 0.05095 0.04643 0.0266 0.0354 1.0000
17.750 1.5501 0.05657 0.05218 0.0245 0.0344 1.0000
18.000 1.5247 0.06321 0.05896 0.0218 0.0339 1.0000
18.250 1.4956 0.07066 0.06657 0.0187 0.0337 1.0000
18.500 1.4632 0.07865 0.07472 0.0153 0.0337 1.0000
18.750 1.4250 0.08774 0.08397 0.0114 0.0337 1.0000
19.000 1.3894 0.09654 0.09293 0.0076 0.0340 1.0000
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Polar data table (+)
Polar graphs
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