USA 49 AIRFOIL (usa49-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 49 AIRFOIL (usa49-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.03 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa49-il-1000000.txt Download as CSV file: xf-usa49-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: USA 49 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6084 0.08854 0.08702 0.0057 1.0000 0.0079
-8.250 -0.6089 0.08385 0.08234 0.0022 1.0000 0.0081
-8.000 -0.6109 0.07851 0.07703 -0.0033 1.0000 0.0083
-7.750 -0.6065 0.07187 0.07035 -0.0112 1.0000 0.0086
-5.000 -0.4529 0.01740 0.01309 -0.0202 1.0000 0.0095
-4.750 -0.4280 0.01422 0.00950 -0.0195 0.9992 0.0088
-4.500 -0.3957 0.01273 0.00779 -0.0203 0.9975 0.0092
-4.250 -0.3622 0.01209 0.00704 -0.0214 0.9959 0.0098
-4.000 -0.3291 0.01107 0.00590 -0.0225 0.9945 0.0103
-3.750 -0.2984 0.00972 0.00446 -0.0233 0.9921 0.0109
-3.500 -0.2657 0.00911 0.00383 -0.0244 0.9896 0.0120
-3.250 -0.2327 0.00863 0.00331 -0.0256 0.9866 0.0130
-3.000 -0.1990 0.00819 0.00283 -0.0268 0.9835 0.0143
-2.750 -0.1691 0.00791 0.00252 -0.0271 0.9767 0.0152
-2.500 -0.1397 0.00748 0.00199 -0.0273 0.9682 0.0173
-2.250 -0.1141 0.00724 0.00171 -0.0265 0.9565 0.0212
-2.000 -0.0886 0.00697 0.00146 -0.0258 0.9456 0.0399
-1.750 -0.0637 0.00651 0.00133 -0.0252 0.9349 0.1303
-1.500 -0.0382 0.00622 0.00121 -0.0247 0.9233 0.1866
-1.250 -0.0136 0.00560 0.00109 -0.0243 0.9101 0.3488
-1.000 0.0110 0.00497 0.00098 -0.0238 0.8949 0.5203
-0.750 0.0348 0.00438 0.00092 -0.0230 0.8765 0.6998
-0.500 0.0555 0.00398 0.00092 -0.0211 0.8419 0.8473
-0.250 0.0785 0.00402 0.00087 -0.0196 0.7887 0.8946
0.000 0.1023 0.00414 0.00085 -0.0184 0.7355 0.9243
0.250 0.1278 0.00428 0.00084 -0.0176 0.6901 0.9480
0.500 0.1575 0.00446 0.00085 -0.0179 0.6414 0.9706
0.750 0.1921 0.00470 0.00087 -0.0194 0.5873 0.9853
1.000 0.2302 0.00493 0.00090 -0.0218 0.5419 0.9952
1.250 0.2689 0.00511 0.00094 -0.0243 0.5091 1.0000
1.500 0.2947 0.00525 0.00097 -0.0240 0.4799 1.0000
1.750 0.3204 0.00541 0.00099 -0.0236 0.4438 1.0000
2.000 0.3459 0.00568 0.00104 -0.0232 0.3894 1.0000
2.250 0.3709 0.00606 0.00114 -0.0229 0.3213 1.0000
2.500 0.3958 0.00656 0.00129 -0.0226 0.2374 1.0000
2.750 0.4190 0.00755 0.00162 -0.0222 0.0791 1.0000
3.000 0.4453 0.00783 0.00181 -0.0219 0.0616 1.0000
3.250 0.4720 0.00805 0.00203 -0.0217 0.0549 1.0000
3.500 0.4989 0.00821 0.00219 -0.0216 0.0535 1.0000
3.750 0.5259 0.00840 0.00241 -0.0214 0.0515 1.0000
4.000 0.5528 0.00862 0.00265 -0.0213 0.0496 1.0000
4.250 0.5797 0.00887 0.00291 -0.0211 0.0480 1.0000
4.500 0.6065 0.00914 0.00321 -0.0210 0.0467 1.0000
4.750 0.6330 0.00947 0.00358 -0.0208 0.0449 1.0000
5.000 0.6588 0.00998 0.00415 -0.0206 0.0419 1.0000
5.250 0.6862 0.01006 0.00423 -0.0206 0.0411 1.0000
5.500 0.7135 0.01016 0.00434 -0.0205 0.0395 1.0000
5.750 0.7406 0.01031 0.00452 -0.0205 0.0374 1.0000
6.000 0.7677 0.01047 0.00467 -0.0205 0.0350 1.0000
6.250 0.7933 0.01097 0.00520 -0.0202 0.0308 1.0000
6.500 0.8217 0.01080 0.00500 -0.0204 0.0292 1.0000
6.750 0.8490 0.01088 0.00499 -0.0205 0.0223 1.0000
7.000 0.8748 0.01131 0.00535 -0.0202 0.0151 1.0000
7.250 0.9006 0.01172 0.00582 -0.0200 0.0132 1.0000
7.500 0.9253 0.01236 0.00650 -0.0196 0.0110 1.0000
7.750 0.9497 0.01305 0.00729 -0.0191 0.0098 1.0000
8.000 0.9746 0.01356 0.00788 -0.0188 0.0091 1.0000
8.250 0.9989 0.01418 0.00859 -0.0184 0.0084 1.0000
8.500 1.0228 0.01485 0.00934 -0.0179 0.0078 1.0000
8.750 1.0449 0.01581 0.01041 -0.0172 0.0072 1.0000
9.000 1.0607 0.01799 0.01286 -0.0156 0.0066 1.0000
9.250 1.0830 0.01887 0.01386 -0.0150 0.0064 1.0000
9.500 1.1052 0.01971 0.01482 -0.0144 0.0062 1.0000
9.750 1.1259 0.02079 0.01605 -0.0136 0.0059 1.0000
10.000 1.1457 0.02197 0.01738 -0.0127 0.0056 1.0000
10.250 1.1653 0.02308 0.01865 -0.0119 0.0053 1.0000
10.500 1.1847 0.02411 0.01980 -0.0111 0.0050 1.0000
10.750 1.2028 0.02524 0.02105 -0.0102 0.0048 1.0000
11.000 1.2180 0.02672 0.02268 -0.0091 0.0046 1.0000
11.250 1.2290 0.02869 0.02485 -0.0076 0.0045 1.0000
11.500 1.2340 0.03128 0.02769 -0.0057 0.0044 1.0000
11.750 1.2313 0.03445 0.03115 -0.0033 0.0043 1.0000
12.000 1.2195 0.03762 0.03458 -0.0001 0.0042 1.0000
12.250 1.2041 0.04114 0.03834 0.0020 0.0042 1.0000
12.500 1.1875 0.04549 0.04291 0.0020 0.0042 1.0000
12.750 1.1720 0.05080 0.04842 -0.0005 0.0042 1.0000
13.000 1.1561 0.05748 0.05529 -0.0053 0.0042 1.0000
13.250 1.1415 0.06497 0.06295 -0.0112 0.0042 1.0000
13.500 1.1242 0.07355 0.07167 -0.0175 0.0043 1.0000
13.750 1.1058 0.08281 0.08106 -0.0237 0.0043 1.0000
14.000 1.0772 0.09463 0.09303 -0.0306 0.0044 1.0000
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Polar data table (+)
Polar graphs
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