BOEING-VERTOL V23010-1.58 AIRFOIL (v23010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL V23010-1.58 AIRFOIL (v23010-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.57 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v23010-il-1000000.txt Download as CSV file: xf-v23010-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL V23010-1.58 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5428 0.08324 0.08151 -0.0142 1.0000 0.0191
-9.250 -0.5460 0.07831 0.07660 -0.0177 1.0000 0.0192
-9.000 -0.5644 0.07009 0.06837 -0.0269 1.0000 0.0192
-8.750 -0.5830 0.06595 0.06417 -0.0279 1.0000 0.0193
-8.500 -0.5924 0.06208 0.06023 -0.0280 1.0000 0.0194
-8.250 -0.5957 0.05854 0.05661 -0.0278 1.0000 0.0195
-8.000 -0.5946 0.05544 0.05342 -0.0272 1.0000 0.0197
-7.750 -0.5918 0.05227 0.05015 -0.0263 1.0000 0.0200
-7.500 -0.5870 0.04920 0.04696 -0.0251 1.0000 0.0204
-7.250 -0.5812 0.04592 0.04353 -0.0235 1.0000 0.0211
-7.000 -0.5590 0.02508 0.02230 -0.0211 1.0000 0.0225
-6.750 -0.5488 0.02301 0.02018 -0.0194 1.0000 0.0227
-6.500 -0.5384 0.02128 0.01838 -0.0175 1.0000 0.0228
-6.250 -0.5090 0.01910 0.01611 -0.0195 0.9961 0.0231
-6.000 -0.5178 0.03056 0.02723 -0.0166 0.9958 0.0233
-5.750 -0.4861 0.02870 0.02524 -0.0184 0.9906 0.0237
-5.500 -0.4539 0.02673 0.02311 -0.0199 0.9851 0.0244
-5.250 -0.4178 0.02556 0.02153 -0.0204 0.9768 0.0264
-5.000 -0.3899 0.02116 0.01684 -0.0218 0.9661 0.0271
-4.750 -0.3568 0.01995 0.01559 -0.0234 0.9514 0.0275
-4.500 -0.3267 0.01904 0.01458 -0.0240 0.9254 0.0281
-4.250 -0.3019 0.01822 0.01358 -0.0233 0.8887 0.0288
-4.000 -0.2761 0.01869 0.01372 -0.0218 0.8586 0.0312
-3.750 -0.2549 0.01610 0.01088 -0.0207 0.8335 0.0324
-3.500 -0.2293 0.01367 0.00804 -0.0191 0.8040 0.0267
-3.250 -0.2048 0.01241 0.00668 -0.0182 0.7764 0.0255
-3.000 -0.1797 0.01160 0.00574 -0.0174 0.7568 0.0252
-2.750 -0.1546 0.01095 0.00500 -0.0167 0.7406 0.0250
-2.500 -0.1290 0.01054 0.00452 -0.0160 0.7250 0.0254
-2.250 -0.1035 0.01014 0.00404 -0.0153 0.7086 0.0256
-2.000 -0.0783 0.00975 0.00359 -0.0146 0.6896 0.0257
-1.750 -0.0530 0.00948 0.00323 -0.0139 0.6650 0.0260
-1.500 -0.0276 0.00932 0.00294 -0.0132 0.6310 0.0263
-1.250 -0.0028 0.00914 0.00262 -0.0124 0.5939 0.0266
-1.000 0.0217 0.00890 0.00223 -0.0116 0.5596 0.0272
-0.750 0.0472 0.00881 0.00202 -0.0110 0.5228 0.0278
-0.500 0.0727 0.00883 0.00188 -0.0104 0.4762 0.0285
-0.250 0.0980 0.00893 0.00177 -0.0099 0.4210 0.0292
0.000 0.1237 0.00903 0.00170 -0.0094 0.3748 0.0302
0.250 0.1499 0.00912 0.00165 -0.0089 0.3399 0.0313
0.500 0.1762 0.00913 0.00156 -0.0085 0.3124 0.0337
0.750 0.2029 0.00918 0.00153 -0.0082 0.2918 0.0368
1.000 0.2296 0.00917 0.00151 -0.0078 0.2782 0.0522
1.250 0.2443 0.00758 0.00138 -0.0059 0.2698 0.5678
1.500 0.2660 0.00717 0.00143 -0.0045 0.2641 0.7123
1.750 0.2887 0.00700 0.00150 -0.0032 0.2577 0.7963
2.000 0.3113 0.00686 0.00159 -0.0018 0.2522 0.8711
2.250 0.3394 0.00681 0.00170 -0.0014 0.2476 0.9330
2.500 0.3768 0.00694 0.00181 -0.0032 0.2426 0.9589
2.750 0.4189 0.00712 0.00195 -0.0061 0.2371 0.9747
3.000 0.4583 0.00723 0.00205 -0.0084 0.2342 0.9839
3.250 0.4974 0.00734 0.00213 -0.0108 0.2305 0.9873
3.500 0.5324 0.00746 0.00221 -0.0123 0.2266 0.9904
3.750 0.5660 0.00764 0.00234 -0.0135 0.2217 0.9937
4.000 0.6033 0.00770 0.00240 -0.0155 0.2192 0.9960
4.250 0.6408 0.00777 0.00247 -0.0175 0.2156 0.9984
4.500 0.6756 0.00788 0.00254 -0.0190 0.2108 1.0000
4.750 0.6983 0.00804 0.00267 -0.0180 0.2062 1.0000
5.000 0.7223 0.00810 0.00275 -0.0171 0.2037 1.0000
5.250 0.7463 0.00818 0.00284 -0.0163 0.1999 1.0000
5.500 0.7700 0.00831 0.00294 -0.0154 0.1943 1.0000
5.750 0.7940 0.00844 0.00305 -0.0146 0.1885 1.0000
6.000 0.8183 0.00855 0.00316 -0.0138 0.1820 1.0000
6.250 0.8423 0.00871 0.00328 -0.0130 0.1735 1.0000
6.500 0.8661 0.00891 0.00342 -0.0122 0.1629 1.0000
6.750 0.8898 0.00912 0.00358 -0.0113 0.1519 1.0000
7.000 0.9132 0.00938 0.00379 -0.0105 0.1405 1.0000
7.250 0.9366 0.00964 0.00401 -0.0097 0.1321 1.0000
7.500 0.9601 0.00991 0.00425 -0.0088 0.1261 1.0000
7.750 0.9839 0.01015 0.00450 -0.0081 0.1211 1.0000
8.000 1.0078 0.01039 0.00473 -0.0073 0.1170 1.0000
8.250 1.0311 0.01068 0.00501 -0.0065 0.1122 1.0000
8.500 1.0551 0.01091 0.00526 -0.0058 0.1083 1.0000
8.750 1.0791 0.01115 0.00551 -0.0051 0.1041 1.0000
9.000 1.1021 0.01149 0.00582 -0.0043 0.0983 1.0000
9.250 1.1263 0.01170 0.00606 -0.0037 0.0935 1.0000
9.500 1.1491 0.01206 0.00639 -0.0029 0.0842 1.0000
9.750 1.1695 0.01268 0.00685 -0.0019 0.0636 1.0000
10.000 1.1874 0.01355 0.00758 -0.0005 0.0446 1.0000
10.250 1.2074 0.01419 0.00819 0.0006 0.0377 1.0000
10.500 1.2281 0.01474 0.00876 0.0016 0.0339 1.0000
10.750 1.2488 0.01529 0.00932 0.0027 0.0315 1.0000
11.000 1.2685 0.01591 0.00996 0.0038 0.0293 1.0000
11.250 1.2897 0.01635 0.01047 0.0047 0.0282 1.0000
11.500 1.3096 0.01690 0.01105 0.0057 0.0269 1.0000
11.750 1.3271 0.01763 0.01182 0.0071 0.0254 1.0000
12.000 1.3454 0.01825 0.01250 0.0083 0.0244 1.0000
12.250 1.3646 0.01875 0.01306 0.0094 0.0235 1.0000
12.500 1.3823 0.01935 0.01370 0.0106 0.0227 1.0000
12.750 1.3976 0.02007 0.01447 0.0122 0.0218 1.0000
13.000 1.4082 0.02105 0.01551 0.0143 0.0210 1.0000
13.250 1.4186 0.02184 0.01639 0.0165 0.0204 1.0000
13.500 1.4292 0.02247 0.01708 0.0188 0.0199 1.0000
13.750 1.4376 0.02323 0.01791 0.0212 0.0194 1.0000
14.000 1.4449 0.02411 0.01886 0.0234 0.0189 1.0000
14.250 1.4516 0.02512 0.01993 0.0253 0.0184 1.0000
14.500 1.4553 0.02642 0.02128 0.0271 0.0179 1.0000
14.750 1.4518 0.02840 0.02336 0.0288 0.0174 1.0000
15.000 1.4451 0.03100 0.02608 0.0296 0.0171 1.0000
15.250 1.4436 0.03351 0.02871 0.0297 0.0169 1.0000
15.500 1.4458 0.03589 0.03118 0.0293 0.0167 1.0000
15.750 1.4423 0.03915 0.03457 0.0283 0.0165 1.0000
16.000 1.4373 0.04293 0.03847 0.0267 0.0162 1.0000
16.250 1.4255 0.04796 0.04363 0.0241 0.0161 1.0000
16.500 1.4091 0.05398 0.04980 0.0209 0.0160 1.0000
16.750 1.3842 0.06152 0.05750 0.0168 0.0160 1.0000
17.000 1.3569 0.06942 0.06555 0.0129 0.0160 1.0000
17.250 1.3271 0.07754 0.07381 0.0089 0.0160 1.0000
17.500 1.2983 0.08553 0.08192 0.0051 0.0161 1.0000
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Polar data table (+)
Polar graphs
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