HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Reynolds number: 200,000 Max Cl/Cd: 49.94 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hsnlf213-il-200000-n5.txt Download as CSV file: xf-hsnlf213-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6401 0.08700 0.08328 -0.0194 0.8225 0.0152
-10.750 -0.6871 0.07173 0.06780 -0.0300 0.8208 0.0146
-10.500 -0.7196 0.06399 0.05981 -0.0324 0.8186 0.0144
-10.250 -0.7403 0.05882 0.05443 -0.0327 0.8157 0.0145
-10.000 -0.7543 0.05485 0.05023 -0.0316 0.8127 0.0147
-9.750 -0.7639 0.05121 0.04632 -0.0298 0.8102 0.0151
-9.500 -0.7703 0.04684 0.04155 -0.0280 0.8081 0.0156
-9.250 -0.7741 0.04201 0.03618 -0.0258 0.8063 0.0161
-9.000 -0.7709 0.03765 0.03123 -0.0237 0.8046 0.0164
-8.750 -0.7603 0.03400 0.02698 -0.0221 0.8029 0.0168
-8.500 -0.7435 0.03133 0.02385 -0.0211 0.8010 0.0172
-8.250 -0.7228 0.02979 0.02217 -0.0208 0.7991 0.0177
-8.000 -0.7007 0.02857 0.02081 -0.0204 0.7971 0.0182
-7.750 -0.6778 0.02754 0.01961 -0.0201 0.7951 0.0192
-7.500 -0.6543 0.02630 0.01813 -0.0197 0.7933 0.0203
-7.250 -0.6298 0.02496 0.01652 -0.0192 0.7918 0.0211
-7.000 -0.6052 0.02367 0.01508 -0.0189 0.7904 0.0218
-6.750 -0.5811 0.02270 0.01406 -0.0186 0.7892 0.0226
-6.500 -0.5561 0.02187 0.01319 -0.0184 0.7877 0.0236
-6.250 -0.5309 0.02109 0.01234 -0.0183 0.7861 0.0248
-6.000 -0.5054 0.02046 0.01161 -0.0181 0.7843 0.0266
-5.750 -0.4817 0.01967 0.01083 -0.0178 0.7824 0.0283
-5.500 -0.4572 0.01907 0.01021 -0.0175 0.7806 0.0300
-5.250 -0.4328 0.01849 0.00958 -0.0172 0.7789 0.0320
-5.000 -0.4087 0.01792 0.00899 -0.0168 0.7775 0.0348
-4.750 -0.3838 0.01748 0.00852 -0.0166 0.7762 0.0382
-4.500 -0.3589 0.01704 0.00802 -0.0163 0.7750 0.0417
-4.250 -0.3341 0.01662 0.00760 -0.0160 0.7738 0.0478
-4.000 -0.3086 0.01621 0.00722 -0.0160 0.7722 0.0566
-3.750 -0.2828 0.01581 0.00688 -0.0160 0.7701 0.0729
-3.500 -0.2582 0.01530 0.00656 -0.0159 0.7683 0.1091
-3.250 -0.2363 0.01447 0.00621 -0.0156 0.7666 0.2146
-3.000 -0.2200 0.01308 0.00576 -0.0147 0.7649 0.4257
-2.750 -0.2072 0.01304 0.00703 -0.0102 0.7632 0.6776
-2.500 -0.1786 0.01335 0.00711 -0.0107 0.7616 0.7407
-2.250 -0.1536 0.01386 0.00759 -0.0093 0.7602 0.7669
-2.000 -0.1305 0.01437 0.00811 -0.0072 0.7590 0.7897
-1.750 -0.1078 0.01479 0.00855 -0.0049 0.7577 0.8075
-1.500 -0.0811 0.01492 0.00864 -0.0047 0.7554 0.8169
-1.250 -0.0535 0.01494 0.00863 -0.0047 0.7532 0.8196
-1.000 -0.0255 0.01496 0.00860 -0.0049 0.7513 0.8222
-0.750 0.0028 0.01494 0.00853 -0.0052 0.7493 0.8241
-0.500 0.0313 0.01490 0.00843 -0.0056 0.7475 0.8258
-0.250 0.0599 0.01486 0.00834 -0.0060 0.7458 0.8274
0.000 0.0886 0.01482 0.00824 -0.0065 0.7442 0.8288
0.250 0.1173 0.01479 0.00815 -0.0069 0.7428 0.8301
0.500 0.1466 0.01484 0.00822 -0.0078 0.7394 0.8310
0.750 0.1754 0.01487 0.00824 -0.0084 0.7363 0.8320
1.000 0.2038 0.01484 0.00821 -0.0088 0.7334 0.8327
1.250 0.2324 0.01478 0.00814 -0.0090 0.7307 0.8333
1.500 0.2610 0.01469 0.00803 -0.0092 0.7284 0.8337
1.750 0.2893 0.01470 0.00809 -0.0097 0.7240 0.8344
2.000 0.3176 0.01468 0.00811 -0.0100 0.7193 0.8352
2.250 0.3462 0.01457 0.00800 -0.0102 0.7156 0.8358
2.500 0.3750 0.01438 0.00780 -0.0103 0.7123 0.8362
2.750 0.4031 0.01435 0.00785 -0.0107 0.7044 0.8367
3.000 0.4319 0.01407 0.00757 -0.0107 0.6986 0.8371
3.250 0.4600 0.01388 0.00745 -0.0108 0.6887 0.8377
3.500 0.4884 0.01355 0.00713 -0.0106 0.6788 0.8385
3.750 0.5168 0.01328 0.00690 -0.0107 0.6672 0.8391
4.000 0.5452 0.01311 0.00681 -0.0109 0.6526 0.8395
4.250 0.5733 0.01296 0.00674 -0.0110 0.6311 0.8399
4.500 0.6012 0.01271 0.00645 -0.0109 0.5964 0.8402
4.750 0.6267 0.01255 0.00597 -0.0101 0.5290 0.8406
5.000 0.6466 0.01317 0.00605 -0.0090 0.4353 0.8412
5.250 0.6647 0.01413 0.00655 -0.0082 0.3475 0.8421
5.500 0.6827 0.01512 0.00713 -0.0075 0.2683 0.8429
5.750 0.7017 0.01600 0.00770 -0.0071 0.2068 0.8434
6.000 0.7215 0.01680 0.00825 -0.0067 0.1598 0.8439
6.250 0.7421 0.01750 0.00879 -0.0063 0.1270 0.8443
6.500 0.7630 0.01816 0.00934 -0.0060 0.1036 0.8447
6.750 0.7842 0.01878 0.00989 -0.0056 0.0874 0.8452
7.000 0.8052 0.01939 0.01047 -0.0052 0.0763 0.8458
7.250 0.8252 0.02007 0.01111 -0.0048 0.0678 0.8465
7.750 0.8639 0.02141 0.01248 -0.0036 0.0564 0.8476
8.000 0.8824 0.02201 0.01317 -0.0028 0.0529 0.8481
8.250 0.8991 0.02271 0.01393 -0.0019 0.0500 0.8486
8.500 0.9155 0.02359 0.01484 -0.0012 0.0475 0.8492
8.750 0.9312 0.02459 0.01588 -0.0004 0.0456 0.8498
9.000 0.9490 0.02542 0.01681 0.0002 0.0439 0.8504
9.250 0.9663 0.02629 0.01776 0.0008 0.0421 0.8510
9.500 0.9832 0.02718 0.01872 0.0015 0.0404 0.8517
9.750 0.9990 0.02816 0.01975 0.0021 0.0390 0.8524
10.000 1.0131 0.02935 0.02096 0.0030 0.0378 0.8531
10.250 1.0286 0.03049 0.02216 0.0039 0.0369 0.8539
10.500 1.0452 0.03151 0.02332 0.0046 0.0361 0.8547
10.750 1.0615 0.03260 0.02454 0.0054 0.0352 0.8555
11.000 1.0774 0.03372 0.02577 0.0061 0.0342 0.8564
11.250 1.0925 0.03487 0.02702 0.0068 0.0332 0.8575
11.500 1.1067 0.03606 0.02830 0.0074 0.0323 0.8588
11.750 1.1202 0.03732 0.02964 0.0081 0.0315 0.8602
12.000 1.1331 0.03870 0.03111 0.0088 0.0309 0.8615
12.500 1.1575 0.04201 0.03464 0.0105 0.0298 0.8638
12.750 1.1671 0.04374 0.03659 0.0114 0.0294 0.8653
13.000 1.1748 0.04564 0.03872 0.0122 0.0289 0.8671
13.250 1.1804 0.04770 0.04101 0.0131 0.0284 0.8691
13.500 1.1839 0.04993 0.04346 0.0139 0.0278 0.8713
13.750 1.1855 0.05232 0.04608 0.0146 0.0273 0.8741
14.000 1.1854 0.05488 0.04885 0.0151 0.0268 0.8771
14.250 1.1835 0.05761 0.05180 0.0156 0.0264 0.8811
14.500 1.1795 0.06059 0.05499 0.0160 0.0261 0.8865
15.000 1.1649 0.06735 0.06221 0.0162 0.0256 0.9084
15.250 1.1525 0.07108 0.06618 0.0160 0.0255 1.0000
15.500 1.1416 0.07568 0.07096 0.0147 0.0253 1.0000
15.750 1.1285 0.08092 0.07640 0.0127 0.0251 1.0000
16.000 1.1120 0.08706 0.08273 0.0100 0.0250 1.0000
16.250 1.0907 0.09456 0.09046 0.0061 0.0250 1.0000
16.500 1.0597 0.10472 0.10088 0.0001 0.0250 1.0000
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Polar data table (+)
Polar graphs
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