USA 46 AIRFOIL (usa46-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 46 AIRFOIL (usa46-il) Reynolds number: 100,000 Max Cl/Cd: 51.82 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa46-il-100000-n5.txt Download as CSV file: xf-usa46-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 46 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5078 0.08777 0.08288 -0.0154 1.0000 0.0229
-8.250 -0.5088 0.08363 0.07881 -0.0173 1.0000 0.0228
-8.000 -0.5121 0.07932 0.07459 -0.0193 1.0000 0.0228
-7.750 -0.5131 0.07440 0.06973 -0.0229 1.0000 0.0227
-7.500 -0.5110 0.06862 0.06400 -0.0284 1.0000 0.0226
-7.250 -0.5061 0.06180 0.05718 -0.0352 1.0000 0.0224
-7.000 -0.4994 0.05325 0.04851 -0.0426 1.0000 0.0223
-6.750 -0.4910 0.04302 0.03786 -0.0498 1.0000 0.0222
-6.500 -0.4772 0.03459 0.02863 -0.0542 1.0000 0.0225
-6.250 -0.4576 0.02909 0.02224 -0.0557 1.0000 0.0235
-6.000 -0.4362 0.02697 0.01991 -0.0559 1.0000 0.0260
-5.750 -0.4131 0.02488 0.01742 -0.0557 1.0000 0.0294
-5.500 -0.3890 0.02221 0.01412 -0.0553 1.0000 0.0330
-5.250 -0.3655 0.02119 0.01304 -0.0550 1.0000 0.0395
-5.000 -0.3414 0.01972 0.01134 -0.0544 1.0000 0.0475
-4.750 -0.3171 0.01880 0.01017 -0.0540 1.0000 0.0592
-4.500 -0.2929 0.01813 0.00932 -0.0535 1.0000 0.0718
-4.250 -0.2687 0.01734 0.00842 -0.0528 1.0000 0.0798
-4.000 -0.2447 0.01670 0.00771 -0.0522 1.0000 0.0888
-3.750 -0.2206 0.01613 0.00704 -0.0515 1.0000 0.0983
-3.500 -0.1966 0.01561 0.00645 -0.0508 1.0000 0.1072
-3.250 -0.1727 0.01516 0.00598 -0.0501 1.0000 0.1183
-3.000 -0.1489 0.01480 0.00559 -0.0494 1.0000 0.1338
-2.750 -0.1252 0.01453 0.00527 -0.0487 1.0000 0.1535
-2.500 -0.1019 0.01422 0.00495 -0.0480 1.0000 0.1710
-2.250 -0.0789 0.01396 0.00471 -0.0473 1.0000 0.1906
-2.000 -0.0559 0.01375 0.00450 -0.0466 1.0000 0.2100
-1.750 -0.0305 0.01350 0.00433 -0.0465 0.9989 0.2325
-1.500 0.0066 0.01319 0.00417 -0.0488 0.9904 0.2700
-1.250 0.0427 0.01273 0.00406 -0.0509 0.9819 0.3479
-1.000 0.0769 0.01196 0.00410 -0.0524 0.9740 0.5665
-0.750 0.1085 0.01152 0.00416 -0.0525 0.9648 0.7488
-0.500 0.1448 0.01112 0.00399 -0.0536 0.9546 0.8597
-0.250 0.1942 0.01091 0.00377 -0.0578 0.9417 1.0000
0.000 0.2351 0.01089 0.00363 -0.0602 0.9259 1.0000
0.250 0.2733 0.01086 0.00352 -0.0620 0.9063 1.0000
0.500 0.3102 0.01085 0.00343 -0.0634 0.8858 1.0000
0.750 0.3436 0.01088 0.00338 -0.0642 0.8649 1.0000
1.000 0.3752 0.01093 0.00339 -0.0646 0.8442 1.0000
1.250 0.4050 0.01100 0.00342 -0.0646 0.8218 1.0000
1.500 0.4343 0.01110 0.00347 -0.0645 0.7989 1.0000
1.750 0.4622 0.01121 0.00357 -0.0641 0.7739 1.0000
2.000 0.4897 0.01134 0.00367 -0.0636 0.7480 1.0000
2.250 0.5169 0.01149 0.00379 -0.0631 0.7215 1.0000
2.500 0.5436 0.01167 0.00397 -0.0624 0.6942 1.0000
2.750 0.5700 0.01188 0.00415 -0.0618 0.6662 1.0000
3.000 0.5961 0.01212 0.00436 -0.0611 0.6373 1.0000
3.250 0.6218 0.01238 0.00464 -0.0603 0.6077 1.0000
3.500 0.6472 0.01269 0.00492 -0.0595 0.5757 1.0000
3.750 0.6720 0.01305 0.00524 -0.0586 0.5412 1.0000
4.000 0.6965 0.01344 0.00560 -0.0576 0.5019 1.0000
4.250 0.7184 0.01396 0.00588 -0.0563 0.4284 1.0000
4.500 0.7390 0.01474 0.00626 -0.0550 0.3435 1.0000
4.750 0.7586 0.01586 0.00682 -0.0538 0.2328 1.0000
5.000 0.7740 0.01810 0.00794 -0.0525 0.0588 1.0000
5.250 0.7953 0.01954 0.00930 -0.0514 0.0357 1.0000
5.500 0.8173 0.02073 0.01060 -0.0503 0.0295 1.0000
5.750 0.8391 0.02191 0.01206 -0.0492 0.0266 1.0000
6.000 0.8599 0.02317 0.01344 -0.0481 0.0233 1.0000
6.250 0.8778 0.02502 0.01536 -0.0466 0.0210 1.0000
6.500 0.8988 0.02670 0.01719 -0.0453 0.0202 1.0000
6.750 0.9208 0.02866 0.01933 -0.0442 0.0196 1.0000
7.000 0.9434 0.03091 0.02182 -0.0430 0.0190 1.0000
7.250 0.9653 0.03321 0.02445 -0.0419 0.0178 1.0000
7.500 0.9853 0.03567 0.02728 -0.0407 0.0165 1.0000
7.750 1.0030 0.03865 0.03068 -0.0393 0.0161 1.0000
8.000 1.0176 0.04203 0.03464 -0.0377 0.0159 1.0000
8.250 1.0281 0.04577 0.03887 -0.0360 0.0159 1.0000
8.500 1.0345 0.04973 0.04331 -0.0343 0.0159 1.0000
8.750 1.0362 0.05393 0.04795 -0.0326 0.0160 1.0000
9.000 1.0331 0.05818 0.05259 -0.0311 0.0162 1.0000
9.250 1.0247 0.06247 0.05720 -0.0298 0.0163 1.0000
9.500 1.0101 0.06652 0.06149 -0.0284 0.0165 1.0000
9.750 0.9918 0.07074 0.06589 -0.0281 0.0166 1.0000
10.000 0.9731 0.07576 0.07107 -0.0301 0.0167 1.0000
10.250 0.9529 0.08237 0.07781 -0.0347 0.0168 1.0000
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Polar data table (+)
Polar graphs
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