BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Reynolds number: 100,000 Max Cl/Cd: 36.63 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v13009-il-100000.txt Download as CSV file: xf-v13009-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5694 0.09454 0.08954 0.0027 1.0000 0.1151
-8.250 -0.5734 0.09043 0.08549 -0.0009 1.0000 0.1195
-8.000 -0.6130 0.08469 0.07963 -0.0154 1.0000 0.1230
-7.750 -0.5936 0.07960 0.07469 -0.0123 1.0000 0.1255
-7.500 -0.5784 0.07677 0.07190 -0.0101 1.0000 0.1293
-7.250 -0.6025 0.07283 0.06748 -0.0189 1.0000 0.1389
-7.000 -0.5789 0.06770 0.06267 -0.0161 1.0000 0.1416
-6.750 -0.5653 0.06472 0.05971 -0.0153 1.0000 0.1471
-6.500 -0.5628 0.06049 0.05528 -0.0174 1.0000 0.1571
-6.250 -0.5483 0.05766 0.05245 -0.0167 1.0000 0.1650
-6.000 -0.5384 0.05416 0.04887 -0.0167 1.0000 0.1756
-5.750 -0.5271 0.05118 0.04581 -0.0164 1.0000 0.1903
-5.500 -0.5140 0.04860 0.04321 -0.0153 1.0000 0.2076
-5.250 -0.4879 0.03595 0.02836 -0.0171 1.0000 0.0954
-5.000 -0.4669 0.03285 0.02500 -0.0158 1.0000 0.0898
-4.750 -0.4464 0.02986 0.02165 -0.0144 1.0000 0.0870
-4.500 -0.4247 0.02746 0.01886 -0.0129 1.0000 0.0865
-4.250 -0.4023 0.02577 0.01686 -0.0116 1.0000 0.0898
-4.000 -0.3788 0.02420 0.01490 -0.0102 1.0000 0.0925
-3.750 -0.3551 0.02227 0.01277 -0.0092 1.0000 0.0954
-3.500 -0.3320 0.02106 0.01161 -0.0083 1.0000 0.1025
-3.250 -0.3079 0.01985 0.01025 -0.0072 1.0000 0.1099
-3.000 -0.2848 0.01887 0.00932 -0.0062 1.0000 0.1203
-2.750 -0.2618 0.01785 0.00841 -0.0053 1.0000 0.1318
-2.500 -0.2392 0.01699 0.00766 -0.0042 1.0000 0.1456
-2.250 -0.2173 0.01623 0.00703 -0.0032 1.0000 0.1623
-2.000 -0.1956 0.01554 0.00646 -0.0021 1.0000 0.1842
-1.750 -0.1741 0.01461 0.00590 -0.0012 1.0000 0.2277
-1.500 -0.1095 0.01224 0.00632 -0.0032 1.0000 0.9700
-1.250 -0.0236 0.01226 0.00599 -0.0142 1.0000 1.0000
-1.000 -0.0248 0.01224 0.00592 -0.0100 1.0000 1.0000
-0.750 -0.0254 0.01233 0.00593 -0.0059 1.0000 1.0000
-0.500 -0.0213 0.01251 0.00603 -0.0027 1.0000 1.0000
-0.250 -0.0118 0.01278 0.00621 -0.0007 1.0000 1.0000
0.000 0.0571 0.01299 0.00631 -0.0092 0.9842 1.0000
0.250 0.1268 0.01299 0.00627 -0.0174 0.9651 1.0000
0.500 0.1971 0.01277 0.00603 -0.0252 0.9440 1.0000
0.750 0.2483 0.01255 0.00578 -0.0290 0.9169 1.0000
1.000 0.2874 0.01238 0.00559 -0.0303 0.8874 1.0000
1.250 0.3173 0.01230 0.00544 -0.0297 0.8553 1.0000
1.500 0.3423 0.01228 0.00534 -0.0282 0.8219 1.0000
1.750 0.3653 0.01232 0.00527 -0.0263 0.7873 1.0000
2.000 0.3874 0.01241 0.00522 -0.0242 0.7509 1.0000
2.250 0.4091 0.01254 0.00521 -0.0222 0.7101 1.0000
2.500 0.4309 0.01271 0.00521 -0.0203 0.6673 1.0000
2.750 0.4527 0.01294 0.00523 -0.0185 0.6213 1.0000
3.000 0.4744 0.01326 0.00530 -0.0167 0.5718 1.0000
3.250 0.4959 0.01369 0.00543 -0.0150 0.5195 1.0000
3.500 0.5174 0.01423 0.00565 -0.0135 0.4675 1.0000
3.750 0.5392 0.01484 0.00594 -0.0122 0.4209 1.0000
4.000 0.5618 0.01547 0.00633 -0.0111 0.3830 1.0000
4.250 0.5850 0.01611 0.00677 -0.0102 0.3542 1.0000
4.500 0.6086 0.01673 0.00722 -0.0094 0.3316 1.0000
4.750 0.6327 0.01738 0.00770 -0.0086 0.3136 1.0000
5.000 0.6571 0.01799 0.00825 -0.0080 0.2972 1.0000
5.250 0.6815 0.01862 0.00883 -0.0073 0.2822 1.0000
5.500 0.7059 0.01928 0.00943 -0.0067 0.2678 1.0000
5.750 0.7301 0.01993 0.01009 -0.0060 0.2536 1.0000
6.000 0.7541 0.02061 0.01081 -0.0054 0.2393 1.0000
6.250 0.7780 0.02136 0.01159 -0.0047 0.2254 1.0000
6.500 0.8017 0.02216 0.01241 -0.0040 0.2116 1.0000
6.750 0.8251 0.02305 0.01333 -0.0033 0.1984 1.0000
7.000 0.8485 0.02404 0.01435 -0.0026 0.1862 1.0000
7.250 0.8719 0.02512 0.01536 -0.0020 0.1752 1.0000
7.500 0.8948 0.02610 0.01643 -0.0013 0.1645 1.0000
7.750 0.9167 0.02738 0.01792 -0.0005 0.1546 1.0000
8.000 0.9403 0.02880 0.01921 -0.0001 0.1469 1.0000
8.250 0.9605 0.03003 0.02086 0.0011 0.1387 1.0000
8.500 0.9832 0.03141 0.02214 0.0015 0.1322 1.0000
8.750 1.0014 0.03312 0.02434 0.0028 0.1260 1.0000
9.000 1.0230 0.03443 0.02571 0.0035 0.1211 1.0000
9.250 1.0394 0.03671 0.02831 0.0046 0.1167 1.0000
9.500 1.0539 0.03887 0.03087 0.0058 0.1120 1.0000
9.750 1.0730 0.04054 0.03264 0.0066 0.1085 1.0000
10.000 1.0891 0.04320 0.03540 0.0073 0.1058 1.0000
10.250 1.0880 0.04719 0.04009 0.0093 0.1036 1.0000
10.500 1.0825 0.05156 0.04499 0.0109 0.1015 1.0000
10.750 1.0718 0.05626 0.05011 0.0122 0.1001 1.0000
11.000 1.0464 0.06220 0.05643 0.0130 0.1001 1.0000
11.250 1.0007 0.06958 0.06405 0.0124 0.1016 1.0000
11.500 0.9524 0.07978 0.07437 0.0064 0.1039 1.0000
11.750 0.9199 0.09047 0.08510 -0.0004 0.1054 1.0000
12.000 0.9035 0.09932 0.09396 -0.0048 0.1061 1.0000
12.250 0.8106 0.14068 0.13521 -0.0288 0.1622 1.0000
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Polar data table (+)
Polar graphs
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