HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Reynolds number: 200,000 Max Cl/Cd: 53.81 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hsnlf213-il-200000.txt Download as CSV file: xf-hsnlf213-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HSNLF(1)-0213 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5632 0.10967 0.10644 -0.0236 0.9127 0.0504
-11.000 -0.5808 0.10103 0.09774 -0.0326 0.9090 0.0505
-10.750 -0.5996 0.09508 0.09170 -0.0376 0.9052 0.0506
-10.500 -0.5869 0.08953 0.08628 -0.0357 0.9029 0.0519
-10.250 -0.5695 0.08916 0.08594 -0.0320 0.9000 0.0534
-10.000 -0.5786 0.08359 0.08032 -0.0358 0.8969 0.0540
-9.750 -0.5920 0.07834 0.07499 -0.0391 0.8940 0.0546
-9.500 -0.6056 0.07355 0.07012 -0.0417 0.8905 0.0553
-9.250 -0.6184 0.06956 0.06600 -0.0427 0.8867 0.0563
-9.000 -0.6289 0.06604 0.06231 -0.0424 0.8834 0.0579
-8.250 -0.6326 0.05500 0.05063 -0.0414 0.8761 0.0661
-8.000 -0.6208 0.05243 0.04789 -0.0412 0.8738 0.0697
-7.750 -0.6219 0.04939 0.04420 -0.0395 0.8711 0.0766
-7.500 -0.6034 0.04606 0.04093 -0.0395 0.8689 0.0788
-7.250 -0.5927 0.03473 0.02788 -0.0340 0.8667 0.0403
-7.000 -0.5725 0.03209 0.02489 -0.0330 0.8650 0.0402
-6.750 -0.5480 0.03086 0.02325 -0.0327 0.8632 0.0411
-6.500 -0.5216 0.02840 0.02052 -0.0327 0.8614 0.0410
-6.250 -0.4941 0.02590 0.01781 -0.0328 0.8597 0.0415
-6.000 -0.4660 0.02389 0.01573 -0.0330 0.8579 0.0428
-5.750 -0.4394 0.02292 0.01474 -0.0331 0.8559 0.0451
-5.500 -0.4130 0.02220 0.01396 -0.0329 0.8539 0.0483
-5.250 -0.3864 0.02154 0.01318 -0.0326 0.8523 0.0505
-5.000 -0.3629 0.02025 0.01197 -0.0320 0.8509 0.0540
-4.750 -0.3383 0.01979 0.01151 -0.0318 0.8494 0.0595
-4.500 -0.3139 0.01898 0.01075 -0.0317 0.8473 0.0651
-4.250 -0.2892 0.01851 0.01029 -0.0317 0.8450 0.0742
-4.000 -0.2668 0.01784 0.00969 -0.0313 0.8429 0.0905
-3.750 -0.2517 0.01644 0.00903 -0.0302 0.8409 0.2104
-3.500 -0.2560 0.01538 0.01043 -0.0231 0.8384 0.6902
-3.250 -0.2322 0.01610 0.01085 -0.0221 0.8364 0.7586
-3.000 -0.2096 0.01693 0.01165 -0.0196 0.8350 0.7816
-2.750 -0.1862 0.01756 0.01224 -0.0180 0.8331 0.8014
-2.500 -0.1641 0.01829 0.01300 -0.0154 0.8305 0.8195
-2.250 -0.1424 0.01905 0.01377 -0.0122 0.8281 0.8386
-2.000 -0.1224 0.01981 0.01450 -0.0087 0.8260 0.8627
-1.750 -0.0710 0.02072 0.01537 -0.0094 0.8252 0.8842
-1.500 -0.0529 0.02077 0.01534 -0.0078 0.8227 0.8929
-1.250 -0.0218 0.02071 0.01520 -0.0085 0.8209 0.8960
-1.000 0.0096 0.02071 0.01513 -0.0092 0.8193 0.8986
-0.750 0.0375 0.02083 0.01523 -0.0105 0.8155 0.9021
-0.500 0.0509 0.02091 0.01529 -0.0087 0.8113 0.9078
-0.250 0.0777 0.02089 0.01522 -0.0088 0.8084 0.9112
0.000 0.1091 0.02083 0.01513 -0.0096 0.8060 0.9132
0.250 0.1354 0.02083 0.01509 -0.0094 0.8036 0.9151
0.500 0.1549 0.02105 0.01533 -0.0094 0.7974 0.9178
0.750 0.1736 0.02101 0.01527 -0.0081 0.7932 0.9200
1.000 0.1925 0.02088 0.01512 -0.0063 0.7901 0.9220
1.250 0.2007 0.02109 0.01535 -0.0040 0.7828 0.9246
1.500 0.2252 0.02101 0.01526 -0.0037 0.7782 0.9257
1.750 0.2530 0.02081 0.01506 -0.0034 0.7751 0.9265
2.000 0.2750 0.02097 0.01525 -0.0032 0.7683 0.9279
2.250 0.2996 0.02084 0.01514 -0.0027 0.7627 0.9286
2.500 0.3280 0.02048 0.01479 -0.0022 0.7594 0.9292
2.750 0.3494 0.02053 0.01488 -0.0017 0.7505 0.9306
3.000 0.3777 0.02003 0.01440 -0.0010 0.7456 0.9310
3.250 0.4024 0.01975 0.01415 -0.0004 0.7379 0.9316
3.500 0.4310 0.01904 0.01346 0.0004 0.7308 0.9320
3.750 0.4577 0.01846 0.01291 0.0012 0.7222 0.9329
4.000 0.4870 0.01767 0.01214 0.0019 0.7150 0.9336
4.250 0.5138 0.01712 0.01165 0.0025 0.7057 0.9341
4.500 0.5445 0.01614 0.01066 0.0031 0.6979 0.9344
4.750 0.5715 0.01548 0.01007 0.0036 0.6850 0.9349
5.000 0.5993 0.01484 0.00952 0.0040 0.6719 0.9355
5.250 0.6271 0.01421 0.00897 0.0044 0.6558 0.9364
5.500 0.6541 0.01369 0.00853 0.0047 0.6304 0.9374
5.750 0.6813 0.01313 0.00795 0.0052 0.5850 0.9380
6.000 0.7022 0.01305 0.00726 0.0070 0.4803 0.9387
6.250 0.7133 0.01418 0.00771 0.0088 0.3646 0.9398
6.500 0.7228 0.01552 0.00847 0.0103 0.2588 0.9411
6.750 0.7330 0.01685 0.00932 0.0117 0.1766 0.9429
7.000 0.7459 0.01803 0.01018 0.0128 0.1306 0.9450
7.250 0.7598 0.01914 0.01110 0.0137 0.1078 0.9467
7.500 0.7756 0.02011 0.01200 0.0145 0.0943 0.9485
7.750 0.7940 0.02084 0.01278 0.0151 0.0852 0.9504
8.000 0.8105 0.02190 0.01380 0.0157 0.0786 0.9525
8.250 0.8310 0.02272 0.01467 0.0160 0.0736 0.9546
8.500 0.8505 0.02376 0.01566 0.0165 0.0696 0.9571
8.750 0.8736 0.02484 0.01678 0.0168 0.0664 0.9594
9.000 0.8975 0.02567 0.01771 0.0168 0.0633 0.9622
9.250 0.9216 0.02657 0.01865 0.0167 0.0604 0.9652
9.500 0.9488 0.02775 0.01981 0.0163 0.0581 0.9677
9.750 0.9847 0.02989 0.02202 0.0151 0.0561 0.9679
10.000 1.0107 0.03113 0.02347 0.0147 0.0548 0.9718
10.250 1.0362 0.03252 0.02507 0.0142 0.0532 0.9772
10.500 1.0608 0.03404 0.02678 0.0137 0.0515 0.9862
10.750 1.0839 0.03580 0.02874 0.0133 0.0503 1.0000
11.000 1.1045 0.03774 0.03086 0.0133 0.0494 1.0000
11.250 1.1228 0.03989 0.03321 0.0133 0.0486 1.0000
11.500 1.1391 0.04224 0.03575 0.0135 0.0479 1.0000
11.750 1.1533 0.04535 0.03903 0.0136 0.0470 1.0000
12.000 1.1572 0.05009 0.04408 0.0143 0.0463 1.0000
12.250 1.1507 0.05354 0.04785 0.0162 0.0461 1.0000
12.500 1.1425 0.05654 0.05113 0.0179 0.0460 1.0000
12.750 1.1320 0.06033 0.05517 0.0192 0.0460 1.0000
13.000 1.1205 0.06487 0.05996 0.0201 0.0462 1.0000
13.250 1.1077 0.06816 0.06345 0.0209 0.0463 1.0000
13.500 1.0927 0.07158 0.06708 0.0213 0.0465 1.0000
13.750 1.0728 0.07543 0.07115 0.0213 0.0468 1.0000
14.000 0.7884 0.08922 0.08588 0.0260 0.0525 1.0000
14.250 0.7253 0.10246 0.09926 0.0192 0.0546 1.0000
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Polar data table (+)
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