BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Reynolds number: 200,000 Max Cl/Cd: 41.05 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v13006-il-200000-n5.txt Download as CSV file: xf-v13006-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V13006-.7 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6344 0.09657 0.09302 0.0180 1.0000 0.0235
-8.250 -0.6329 0.09234 0.08881 0.0151 1.0000 0.0239
-8.000 -0.6320 0.08790 0.08441 0.0116 1.0000 0.0242
-7.750 -0.6299 0.08295 0.07947 0.0063 1.0000 0.0245
-7.500 -0.6236 0.07761 0.07410 0.0009 1.0000 0.0249
-7.250 -0.6150 0.07226 0.06868 -0.0039 1.0000 0.0254
-7.000 -0.5945 0.06714 0.06328 -0.0104 1.0000 0.0277
-6.750 -0.5814 0.06277 0.05873 -0.0122 1.0000 0.0278
-6.500 -0.5670 0.05868 0.05442 -0.0135 1.0000 0.0279
-6.000 -0.5467 0.04340 0.03854 -0.0151 1.0000 0.0201
-5.750 -0.5286 0.04050 0.03552 -0.0151 1.0000 0.0188
-5.500 -0.5103 0.03670 0.03145 -0.0150 1.0000 0.0182
-5.250 -0.4901 0.03306 0.02748 -0.0146 1.0000 0.0178
-5.000 -0.4685 0.02966 0.02370 -0.0140 1.0000 0.0174
-4.750 -0.4458 0.02656 0.02018 -0.0132 1.0000 0.0172
-4.500 -0.4221 0.02386 0.01707 -0.0123 1.0000 0.0172
-4.250 -0.3975 0.02159 0.01443 -0.0115 1.0000 0.0175
-4.000 -0.3725 0.01973 0.01223 -0.0107 1.0000 0.0179
-3.750 -0.3467 0.01868 0.01090 -0.0099 1.0000 0.0193
-3.500 -0.3219 0.01710 0.00911 -0.0093 1.0000 0.0204
-3.250 -0.2970 0.01587 0.00778 -0.0086 1.0000 0.0209
-3.000 -0.2721 0.01487 0.00674 -0.0079 1.0000 0.0216
-2.750 -0.2473 0.01404 0.00588 -0.0072 1.0000 0.0226
-2.500 -0.2227 0.01330 0.00512 -0.0065 1.0000 0.0238
-2.250 -0.1982 0.01270 0.00448 -0.0057 1.0000 0.0257
-2.000 -0.1734 0.01228 0.00406 -0.0051 1.0000 0.0284
-1.750 -0.1491 0.01157 0.00334 -0.0044 1.0000 0.0317
-1.500 -0.1241 0.01118 0.00292 -0.0038 1.0000 0.0362
-1.250 -0.0990 0.01081 0.00254 -0.0033 1.0000 0.0456
-1.000 -0.0741 0.01029 0.00230 -0.0029 1.0000 0.1033
-0.750 -0.0517 0.00768 0.00222 -0.0026 0.9936 0.7416
-0.500 0.0069 0.00733 0.00231 -0.0076 0.9968 1.0000
-0.250 0.0476 0.00733 0.00220 -0.0104 0.9788 1.0000
0.000 0.0882 0.00732 0.00211 -0.0131 0.9514 1.0000
0.250 0.1273 0.00731 0.00200 -0.0152 0.9093 1.0000
0.500 0.1584 0.00733 0.00189 -0.0154 0.8599 1.0000
0.750 0.1844 0.00742 0.00182 -0.0145 0.8120 1.0000
1.000 0.2087 0.00756 0.00177 -0.0134 0.7631 1.0000
1.250 0.2326 0.00776 0.00176 -0.0122 0.7106 1.0000
1.500 0.2566 0.00801 0.00177 -0.0111 0.6564 1.0000
1.750 0.2810 0.00828 0.00181 -0.0103 0.6037 1.0000
2.000 0.3057 0.00855 0.00189 -0.0095 0.5538 1.0000
2.250 0.3304 0.00887 0.00200 -0.0088 0.4991 1.0000
2.500 0.3542 0.00937 0.00211 -0.0081 0.4163 1.0000
2.750 0.3784 0.00988 0.00225 -0.0076 0.3364 1.0000
3.000 0.4035 0.01029 0.00244 -0.0072 0.2867 1.0000
3.250 0.4288 0.01069 0.00267 -0.0068 0.2431 1.0000
3.500 0.4541 0.01113 0.00289 -0.0065 0.1900 1.0000
3.750 0.4791 0.01167 0.00318 -0.0062 0.1340 1.0000
4.000 0.5024 0.01273 0.00371 -0.0058 0.0416 1.0000
4.250 0.5278 0.01333 0.00433 -0.0054 0.0298 1.0000
4.500 0.5536 0.01386 0.00496 -0.0049 0.0261 1.0000
4.750 0.5792 0.01440 0.00560 -0.0045 0.0242 1.0000
5.000 0.6045 0.01500 0.00629 -0.0040 0.0229 1.0000
5.250 0.6295 0.01564 0.00702 -0.0036 0.0213 1.0000
5.500 0.6533 0.01656 0.00798 -0.0031 0.0198 1.0000
5.750 0.6777 0.01736 0.00888 -0.0026 0.0191 1.0000
6.000 0.7017 0.01832 0.00993 -0.0020 0.0186 1.0000
6.250 0.7254 0.01940 0.01112 -0.0014 0.0182 1.0000
6.500 0.7490 0.02062 0.01248 -0.0007 0.0178 1.0000
6.750 0.7725 0.02199 0.01399 -0.0001 0.0174 1.0000
7.000 0.7956 0.02352 0.01572 0.0006 0.0172 1.0000
7.250 0.8182 0.02527 0.01771 0.0013 0.0170 1.0000
7.500 0.8399 0.02722 0.01994 0.0021 0.0168 1.0000
7.750 0.8611 0.02891 0.02190 0.0027 0.0162 1.0000
8.000 0.8814 0.03048 0.02368 0.0032 0.0156 1.0000
8.250 0.8998 0.03251 0.02591 0.0037 0.0150 1.0000
8.500 0.9147 0.03552 0.02928 0.0045 0.0148 1.0000
8.750 0.9259 0.03912 0.03329 0.0053 0.0147 1.0000
9.000 0.9338 0.04293 0.03752 0.0060 0.0146 1.0000
9.250 0.9379 0.04694 0.04195 0.0066 0.0146 1.0000
9.500 0.9368 0.05131 0.04669 0.0068 0.0146 1.0000
9.750 0.9302 0.05592 0.05161 0.0065 0.0146 1.0000
10.250 0.9012 0.06582 0.06197 0.0019 0.0147 1.0000
10.500 0.8313 0.09614 0.09260 -0.0241 0.0161 1.0000
10.750 0.8165 0.10531 0.10172 -0.0290 0.0166 1.0000
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Polar data table (+)
Polar graphs
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