USA 49 AIRFOIL (usa49-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 49 AIRFOIL (usa49-il) Reynolds number: 50,000 Max Cl/Cd: 33.62 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa49-il-50000-n5.txt Download as CSV file: xf-usa49-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4381 0.09759 0.09112 -0.0113 1.0000 0.0524
-8.750 -0.4355 0.09336 0.08692 -0.0116 1.0000 0.0497
-8.500 -0.5454 0.10286 0.09613 -0.0020 1.0000 0.0624
-8.250 -0.5452 0.09753 0.09084 -0.0060 1.0000 0.0512
-8.000 -0.5430 0.09316 0.08652 -0.0080 1.0000 0.0484
-7.750 -0.5439 0.08814 0.08158 -0.0124 1.0000 0.0458
-7.500 -0.5418 0.08140 0.07478 -0.0208 1.0000 0.0416
-7.250 -0.5356 0.07723 0.07062 -0.0218 1.0000 0.0405
-7.000 -0.5292 0.07267 0.06603 -0.0239 1.0000 0.0394
-6.750 -0.5217 0.06790 0.06117 -0.0262 1.0000 0.0383
-6.500 -0.5127 0.06298 0.05612 -0.0283 1.0000 0.0373
-6.250 -0.5020 0.05808 0.05101 -0.0301 1.0000 0.0365
-6.000 -0.4893 0.05342 0.04606 -0.0314 1.0000 0.0363
-5.750 -0.4746 0.04911 0.04141 -0.0321 1.0000 0.0366
-5.500 -0.4579 0.04511 0.03702 -0.0323 1.0000 0.0372
-5.250 -0.4394 0.04131 0.03277 -0.0322 1.0000 0.0377
-5.000 -0.4192 0.03772 0.02862 -0.0317 1.0000 0.0378
-4.750 -0.3974 0.03442 0.02479 -0.0310 1.0000 0.0379
-4.500 -0.3742 0.03152 0.02137 -0.0301 1.0000 0.0383
-4.250 -0.3500 0.02900 0.01838 -0.0291 1.0000 0.0393
-4.000 -0.3250 0.02705 0.01592 -0.0280 1.0000 0.0421
-3.750 -0.3019 0.02520 0.01403 -0.0272 1.0000 0.0466
-3.500 -0.2772 0.02366 0.01226 -0.0260 1.0000 0.0505
-3.250 -0.2522 0.02227 0.01059 -0.0249 1.0000 0.0557
-3.000 -0.2278 0.02119 0.00946 -0.0241 1.0000 0.0707
-2.750 -0.2035 0.01990 0.00828 -0.0233 1.0000 0.1047
-2.500 -0.1822 0.01786 0.00740 -0.0230 1.0000 0.2977
-2.250 -0.1397 0.01544 0.00715 -0.0224 1.0000 0.9502
-2.000 -0.0985 0.01531 0.00644 -0.0252 1.0000 1.0000
-1.750 -0.0803 0.01527 0.00605 -0.0237 1.0000 1.0000
-1.500 -0.0614 0.01525 0.00570 -0.0223 1.0000 1.0000
-1.250 -0.0420 0.01527 0.00545 -0.0210 1.0000 1.0000
-1.000 -0.0222 0.01531 0.00526 -0.0199 1.0000 1.0000
-0.750 -0.0020 0.01539 0.00513 -0.0188 1.0000 1.0000
-0.500 0.0185 0.01549 0.00504 -0.0178 1.0000 1.0000
-0.250 0.0391 0.01562 0.00503 -0.0170 1.0000 1.0000
0.000 0.0599 0.01579 0.00508 -0.0162 1.0000 1.0000
0.250 0.0806 0.01600 0.00519 -0.0155 1.0000 1.0000
0.500 0.1012 0.01626 0.00535 -0.0149 1.0000 1.0000
0.750 0.1430 0.01657 0.00560 -0.0185 0.9880 1.0000
1.000 0.1906 0.01684 0.00585 -0.0231 0.9706 1.0000
1.250 0.2399 0.01705 0.00608 -0.0277 0.9528 1.0000
1.500 0.2855 0.01719 0.00628 -0.0314 0.9317 1.0000
1.750 0.3283 0.01728 0.00646 -0.0343 0.9096 1.0000
2.000 0.3664 0.01733 0.00660 -0.0360 0.8853 1.0000
2.500 0.4329 0.01740 0.00690 -0.0371 0.8314 1.0000
2.750 0.4634 0.01745 0.00704 -0.0369 0.8026 1.0000
3.000 0.4920 0.01750 0.00719 -0.0361 0.7708 1.0000
3.250 0.5181 0.01755 0.00724 -0.0346 0.7307 1.0000
3.500 0.5422 0.01767 0.00729 -0.0327 0.6857 1.0000
3.750 0.5651 0.01790 0.00745 -0.0307 0.6385 1.0000
4.000 0.5875 0.01823 0.00773 -0.0289 0.5920 1.0000
4.250 0.6100 0.01862 0.00806 -0.0274 0.5475 1.0000
4.500 0.6317 0.01908 0.00844 -0.0258 0.4985 1.0000
4.750 0.6542 0.01954 0.00895 -0.0246 0.4536 1.0000
5.000 0.6757 0.02010 0.00948 -0.0232 0.3912 1.0000
5.250 0.6954 0.02097 0.01002 -0.0219 0.3057 1.0000
5.500 0.7147 0.02227 0.01087 -0.0209 0.2043 1.0000
5.750 0.7351 0.02377 0.01203 -0.0202 0.1455 1.0000
6.000 0.7569 0.02506 0.01333 -0.0194 0.1253 1.0000
6.250 0.7784 0.02638 0.01478 -0.0185 0.1150 1.0000
6.500 0.8002 0.02771 0.01633 -0.0175 0.1075 1.0000
6.750 0.8214 0.02924 0.01802 -0.0164 0.0983 1.0000
7.000 0.8418 0.03108 0.01995 -0.0153 0.0867 1.0000
7.250 0.8614 0.03331 0.02230 -0.0143 0.0723 1.0000
7.500 0.8816 0.03614 0.02527 -0.0133 0.0607 1.0000
7.750 0.9020 0.03907 0.02847 -0.0123 0.0522 1.0000
8.000 0.9198 0.04230 0.03222 -0.0110 0.0461 1.0000
8.250 0.9361 0.04543 0.03585 -0.0099 0.0417 1.0000
8.500 0.9501 0.04922 0.03981 -0.0091 0.0392 1.0000
8.750 0.9565 0.05302 0.04436 -0.0073 0.0373 1.0000
9.000 0.9590 0.05705 0.04898 -0.0059 0.0354 1.0000
9.250 0.9580 0.06111 0.05347 -0.0048 0.0341 1.0000
9.500 0.9530 0.06529 0.05799 -0.0039 0.0333 1.0000
9.750 0.9428 0.06967 0.06267 -0.0034 0.0330 1.0000
10.000 0.9261 0.07410 0.06731 -0.0032 0.0332 1.0000
10.250 0.9066 0.07934 0.07273 -0.0050 0.0336 1.0000
10.500 0.8868 0.08582 0.07933 -0.0092 0.0343 1.0000
10.750 0.8689 0.09348 0.08704 -0.0149 0.0353 1.0000
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