USA 48 AIRFOIL (usa48-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: USA 48 AIRFOIL (usa48-il) Reynolds number: 200,000 Max Cl/Cd: 69.12 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa48-il-200000.txt Download as CSV file: xf-usa48-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: USA 48 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3559 0.09294 0.08982 -0.0407 1.0000 0.1038
-10.000 -0.6663 0.04688 0.04315 -0.0586 1.0000 0.0501
-9.750 -0.7851 0.05108 0.04643 -0.0493 1.0000 0.0424
-9.500 -0.7957 0.04801 0.04317 -0.0457 1.0000 0.0419
-9.250 -0.8034 0.04507 0.03999 -0.0423 1.0000 0.0414
-9.000 -0.8013 0.04197 0.03653 -0.0404 0.9986 0.0413
-8.750 -0.7759 0.03868 0.03270 -0.0425 0.9929 0.0422
-8.250 -0.7210 0.03300 0.02609 -0.0457 0.9812 0.0450
-8.000 -0.6896 0.03075 0.02375 -0.0474 0.9758 0.0465
-7.750 -0.6528 0.02914 0.02198 -0.0498 0.9721 0.0490
-7.500 -0.6244 0.02799 0.02055 -0.0503 0.9648 0.0514
-7.250 -0.5899 0.02603 0.01837 -0.0519 0.9609 0.0535
-7.000 -0.5524 0.02431 0.01670 -0.0544 0.9585 0.0568
-6.750 -0.5268 0.02329 0.01563 -0.0542 0.9502 0.0598
-6.500 -0.4893 0.02224 0.01446 -0.0563 0.9465 0.0624
-6.250 -0.4632 0.02091 0.01322 -0.0564 0.9397 0.0661
-6.000 -0.4304 0.02004 0.01234 -0.0576 0.9342 0.0698
-5.750 -0.3924 0.01913 0.01142 -0.0599 0.9309 0.0740
-5.500 -0.3685 0.01852 0.01083 -0.0593 0.9217 0.0783
-5.250 -0.3312 0.01789 0.01017 -0.0612 0.9178 0.0845
-5.000 -0.2900 0.01725 0.00952 -0.0638 0.9155 0.0954
-4.750 -0.2684 0.01664 0.00893 -0.0627 0.9053 0.1108
-4.500 -0.2351 0.01532 0.00821 -0.0643 0.9019 0.2194
-4.250 -0.2050 0.01483 0.00788 -0.0648 0.8955 0.2705
-4.000 -0.1713 0.01443 0.00754 -0.0659 0.8896 0.3060
-3.750 -0.1288 0.01400 0.00716 -0.0687 0.8866 0.3376
-3.500 -0.0927 0.01365 0.00686 -0.0703 0.8809 0.3651
-3.250 -0.0597 0.01333 0.00656 -0.0712 0.8735 0.3907
-3.000 -0.0172 0.01289 0.00617 -0.0741 0.8696 0.4181
-2.750 0.0083 0.01259 0.00595 -0.0735 0.8593 0.4450
-2.500 0.0472 0.01210 0.00560 -0.0756 0.8538 0.4852
-2.250 0.0697 0.01177 0.00551 -0.0743 0.8427 0.5313
-2.000 0.1025 0.01156 0.00558 -0.0748 0.8353 0.6066
-1.750 0.1293 0.01160 0.00561 -0.0741 0.8242 0.6569
-1.500 0.1562 0.01165 0.00563 -0.0735 0.8133 0.6884
-1.250 0.1885 0.01164 0.00554 -0.0740 0.8039 0.7123
-1.000 0.2153 0.01163 0.00550 -0.0732 0.7918 0.7318
-0.750 0.2412 0.01159 0.00542 -0.0723 0.7783 0.7490
-0.500 0.2674 0.01156 0.00533 -0.0715 0.7645 0.7649
-0.250 0.2938 0.01153 0.00524 -0.0708 0.7510 0.7785
0.000 0.3199 0.01153 0.00515 -0.0701 0.7377 0.7920
0.250 0.3463 0.01152 0.00507 -0.0694 0.7247 0.8057
0.500 0.3700 0.01151 0.00505 -0.0682 0.7118 0.8184
0.750 0.3936 0.01152 0.00506 -0.0671 0.7000 0.8308
1.000 0.4194 0.01155 0.00506 -0.0664 0.6896 0.8425
1.250 0.4448 0.01158 0.00506 -0.0657 0.6789 0.8534
1.500 0.4694 0.01161 0.00512 -0.0648 0.6677 0.8649
1.750 0.4969 0.01167 0.00517 -0.0645 0.6577 0.8787
2.000 0.5246 0.01174 0.00524 -0.0642 0.6471 0.8934
2.250 0.5538 0.01184 0.00536 -0.0644 0.6361 0.9074
2.500 0.5871 0.01196 0.00544 -0.0654 0.6256 0.9195
2.750 0.6226 0.01207 0.00552 -0.0669 0.6135 0.9287
3.000 0.6555 0.01218 0.00564 -0.0681 0.6010 0.9397
3.250 0.6929 0.01233 0.00578 -0.0702 0.5894 0.9480
3.500 0.7296 0.01248 0.00589 -0.0722 0.5776 0.9569
3.750 0.7680 0.01266 0.00602 -0.0745 0.5656 0.9661
4.000 0.8077 0.01284 0.00621 -0.0772 0.5526 0.9751
4.250 0.8467 0.01302 0.00640 -0.0799 0.5400 0.9852
4.500 0.8858 0.01320 0.00656 -0.0827 0.5261 0.9950
4.750 0.9054 0.01329 0.00660 -0.0818 0.5137 1.0000
5.000 0.9141 0.01339 0.00667 -0.0784 0.5032 1.0000
5.250 0.9284 0.01355 0.00682 -0.0759 0.4918 1.0000
5.500 0.9449 0.01374 0.00698 -0.0738 0.4806 1.0000
5.750 0.9615 0.01396 0.00715 -0.0716 0.4690 1.0000
6.000 0.9767 0.01414 0.00734 -0.0692 0.4555 1.0000
6.250 0.9918 0.01435 0.00754 -0.0667 0.4415 1.0000
6.500 1.0071 0.01457 0.00776 -0.0643 0.4281 1.0000
6.750 1.0223 0.01482 0.00800 -0.0619 0.4148 1.0000
7.000 1.0372 0.01509 0.00825 -0.0595 0.4018 1.0000
7.250 1.0500 0.01539 0.00852 -0.0567 0.3873 1.0000
7.500 1.0602 0.01570 0.00879 -0.0533 0.3715 1.0000
7.750 1.0700 0.01606 0.00911 -0.0500 0.3547 1.0000
8.000 1.0793 0.01648 0.00948 -0.0467 0.3364 1.0000
8.250 1.0883 0.01696 0.00990 -0.0435 0.3176 1.0000
8.500 1.0966 0.01751 0.01038 -0.0402 0.2984 1.0000
8.750 1.1060 0.01808 0.01091 -0.0373 0.2791 1.0000
9.000 1.1141 0.01873 0.01150 -0.0342 0.2568 1.0000
9.250 1.1207 0.01950 0.01218 -0.0311 0.2363 1.0000
9.500 1.1284 0.02029 0.01290 -0.0283 0.2152 1.0000
9.750 1.1364 0.02111 0.01368 -0.0257 0.1995 1.0000
10.000 1.1443 0.02200 0.01452 -0.0232 0.1854 1.0000
10.250 1.1524 0.02291 0.01541 -0.0208 0.1744 1.0000
10.500 1.1589 0.02395 0.01642 -0.0185 0.1635 1.0000
10.750 1.1671 0.02496 0.01744 -0.0164 0.1537 1.0000
11.000 1.1722 0.02618 0.01865 -0.0142 0.1426 1.0000
11.250 1.1756 0.02758 0.02005 -0.0119 0.1311 1.0000
11.500 1.1777 0.02916 0.02162 -0.0098 0.1173 1.0000
12.000 1.1774 0.03300 0.02512 -0.0059 0.0596 1.0000
12.250 1.1700 0.03564 0.02772 -0.0038 0.0534 1.0000
12.500 1.1668 0.03810 0.03029 -0.0023 0.0499 1.0000
12.750 1.1612 0.04088 0.03316 -0.0010 0.0474 1.0000
13.000 1.1505 0.04427 0.03662 0.0002 0.0451 1.0000
13.250 1.1493 0.04689 0.03936 0.0009 0.0434 1.0000
13.500 1.1473 0.04966 0.04225 0.0015 0.0418 1.0000
13.750 1.1440 0.05264 0.04531 0.0020 0.0405 1.0000
14.000 1.1404 0.05572 0.04846 0.0023 0.0394 1.0000
14.250 1.1357 0.05892 0.05169 0.0027 0.0383 1.0000
14.500 1.1333 0.06168 0.05442 0.0035 0.0371 1.0000
14.750 1.1378 0.06396 0.05679 0.0039 0.0362 1.0000
15.000 1.1422 0.06631 0.05925 0.0041 0.0350 1.0000
15.250 1.1474 0.06853 0.06154 0.0045 0.0339 1.0000
15.500 1.1522 0.07081 0.06386 0.0047 0.0326 1.0000
15.750 1.1609 0.07252 0.06555 0.0054 0.0316 1.0000
16.000 1.1909 0.07178 0.06464 0.0085 0.0301 1.0000
16.250 1.1954 0.07429 0.06732 0.0086 0.0298 1.0000
16.500 1.1969 0.07717 0.07038 0.0084 0.0294 1.0000
16.750 1.1982 0.08014 0.07353 0.0082 0.0290 1.0000
17.000 1.1967 0.08348 0.07704 0.0076 0.0283 1.0000
17.250 1.1973 0.08669 0.08043 0.0072 0.0280 1.0000
17.500 1.1951 0.09022 0.08411 0.0064 0.0275 1.0000
17.750 1.1929 0.09376 0.08777 0.0054 0.0268 1.0000
18.000 1.1902 0.09751 0.09167 0.0045 0.0266 1.0000
18.250 1.1896 0.10095 0.09521 0.0036 0.0260 1.0000
18.500 1.1831 0.10542 0.09986 0.0021 0.0260 1.0000
18.750 1.1758 0.11003 0.10462 0.0002 0.0257 1.0000
19.000 1.1640 0.11550 0.11030 -0.0023 0.0258 1.0000
19.250 1.1515 0.12120 0.11618 -0.0051 0.0258 1.0000
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