HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Reynolds number: 100,000 Max Cl/Cd: 37.38 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hsnlf213-il-100000-n5.txt Download as CSV file: xf-hsnlf213-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.3962 0.13727 0.13279 -0.0173 0.9146 0.0543
-13.000 -0.4017 0.13156 0.12702 -0.0193 0.9115 0.0381
-12.500 -0.5569 0.13025 0.12562 -0.0086 1.0000 0.0328
-12.250 -0.5505 0.12678 0.12215 -0.0098 0.9613 0.0320
-12.000 -0.5483 0.12232 0.11767 -0.0119 0.9385 0.0312
-11.750 -0.5491 0.11725 0.11259 -0.0143 0.9269 0.0304
-11.250 -0.5870 0.09305 0.08838 -0.0307 0.9136 0.0267
-11.000 -0.5954 0.08667 0.08194 -0.0350 0.9076 0.0265
-10.750 -0.6085 0.08049 0.07567 -0.0390 0.9019 0.0263
-10.500 -0.6247 0.07499 0.07004 -0.0417 0.8967 0.0261
-10.250 -0.6414 0.07002 0.06490 -0.0434 0.8918 0.0260
-10.000 -0.6571 0.06555 0.06023 -0.0442 0.8866 0.0259
-9.750 -0.6720 0.06165 0.05609 -0.0433 0.8818 0.0258
-9.500 -0.6826 0.05775 0.05189 -0.0421 0.8776 0.0258
-9.250 -0.6880 0.05368 0.04744 -0.0409 0.8733 0.0258
-9.000 -0.6905 0.04963 0.04289 -0.0392 0.8696 0.0263
-8.750 -0.6876 0.04611 0.03887 -0.0376 0.8665 0.0270
-8.500 -0.6720 0.04445 0.03713 -0.0372 0.8640 0.0280
-8.250 -0.6569 0.04216 0.03458 -0.0367 0.8612 0.0289
-8.000 -0.6416 0.03939 0.03140 -0.0358 0.8584 0.0294
-7.750 -0.6238 0.03684 0.02842 -0.0349 0.8557 0.0300
-7.500 -0.6037 0.03453 0.02571 -0.0341 0.8531 0.0307
-7.250 -0.5815 0.03251 0.02328 -0.0333 0.8508 0.0319
-7.000 -0.5575 0.03081 0.02124 -0.0329 0.8485 0.0337
-6.750 -0.5324 0.02958 0.01997 -0.0331 0.8462 0.0356
-6.500 -0.5061 0.02827 0.01851 -0.0331 0.8441 0.0372
-6.250 -0.4796 0.02702 0.01711 -0.0329 0.8420 0.0390
-6.000 -0.4538 0.02597 0.01592 -0.0327 0.8399 0.0418
-5.750 -0.4300 0.02509 0.01508 -0.0324 0.8378 0.0449
-5.500 -0.4062 0.02426 0.01418 -0.0317 0.8358 0.0479
-5.250 -0.3831 0.02348 0.01334 -0.0311 0.8338 0.0517
-5.000 -0.3596 0.02281 0.01268 -0.0310 0.8316 0.0571
-4.750 -0.3363 0.02219 0.01200 -0.0306 0.8294 0.0631
-4.500 -0.3134 0.02162 0.01144 -0.0301 0.8271 0.0732
-4.250 -0.2908 0.02104 0.01089 -0.0295 0.8248 0.0887
-4.000 -0.2698 0.02032 0.01044 -0.0286 0.8226 0.1286
-3.750 -0.2557 0.01908 0.01006 -0.0269 0.8206 0.2878
-3.500 -0.2501 0.01855 0.01144 -0.0206 0.8189 0.6203
-3.250 -0.2313 0.01935 0.01213 -0.0189 0.8160 0.7355
-3.000 -0.2119 0.02001 0.01264 -0.0166 0.8132 0.7725
-2.750 -0.1896 0.02103 0.01366 -0.0127 0.8110 0.8054
-2.500 -0.1617 0.02204 0.01463 -0.0093 0.8095 0.8373
-2.250 -0.1328 0.02232 0.01479 -0.0085 0.8078 0.8515
-2.000 -0.1062 0.02228 0.01461 -0.0084 0.8058 0.8562
-1.750 -0.0867 0.02219 0.01439 -0.0074 0.8036 0.8622
-1.500 -0.0576 0.02226 0.01437 -0.0081 0.8009 0.8656
-1.250 -0.0299 0.02231 0.01434 -0.0084 0.7980 0.8696
-1.000 -0.0062 0.02230 0.01426 -0.0082 0.7951 0.8735
-0.750 0.0138 0.02226 0.01414 -0.0073 0.7925 0.8775
-0.500 0.0398 0.02222 0.01403 -0.0073 0.7903 0.8795
-0.250 0.0663 0.02225 0.01401 -0.0075 0.7877 0.8815
0.000 0.0902 0.02239 0.01413 -0.0076 0.7835 0.8838
0.250 0.1141 0.02244 0.01415 -0.0075 0.7798 0.8860
0.500 0.1383 0.02245 0.01413 -0.0072 0.7769 0.8881
0.750 0.1626 0.02242 0.01407 -0.0068 0.7743 0.8901
1.000 0.1824 0.02259 0.01425 -0.0063 0.7691 0.8922
1.250 0.2045 0.02268 0.01434 -0.0059 0.7644 0.8941
1.500 0.2314 0.02267 0.01434 -0.0059 0.7610 0.8953
1.750 0.2590 0.02261 0.01428 -0.0059 0.7583 0.8962
2.000 0.2797 0.02288 0.01461 -0.0057 0.7508 0.8975
2.250 0.3060 0.02285 0.01462 -0.0055 0.7464 0.8988
2.750 0.3544 0.02298 0.01485 -0.0050 0.7347 0.9015
3.000 0.3820 0.02282 0.01474 -0.0049 0.7300 0.9023
3.250 0.4056 0.02284 0.01484 -0.0045 0.7224 0.9035
3.500 0.4323 0.02261 0.01468 -0.0041 0.7154 0.9048
3.750 0.4569 0.02245 0.01459 -0.0036 0.7065 0.9063
4.000 0.4857 0.02189 0.01411 -0.0030 0.6984 0.9071
4.250 0.5100 0.02154 0.01386 -0.0023 0.6857 0.9082
4.500 0.5356 0.02104 0.01346 -0.0015 0.6721 0.9091
4.750 0.5613 0.02054 0.01307 -0.0008 0.6569 0.9101
5.000 0.5867 0.02006 0.01273 -0.0001 0.6389 0.9114
5.250 0.6083 0.01992 0.01273 0.0007 0.6124 0.9132
5.500 0.6334 0.01941 0.01229 0.0016 0.5766 0.9146
5.750 0.6655 0.01824 0.01084 0.0031 0.5079 0.9151
6.000 0.6851 0.01833 0.01031 0.0052 0.4120 0.9163
6.250 0.6970 0.01930 0.01078 0.0071 0.3254 0.9183
6.500 0.7090 0.02037 0.01143 0.0085 0.2527 0.9205
6.750 0.7223 0.02142 0.01213 0.0097 0.1940 0.9232
7.000 0.7377 0.02238 0.01286 0.0106 0.1527 0.9257
7.250 0.7543 0.02328 0.01361 0.0114 0.1251 0.9280
7.500 0.7706 0.02420 0.01442 0.0122 0.1075 0.9305
7.750 0.7867 0.02506 0.01528 0.0131 0.0951 0.9335
8.000 0.8037 0.02593 0.01620 0.0137 0.0855 0.9369
8.250 0.8197 0.02696 0.01721 0.0144 0.0788 0.9407
8.500 0.8380 0.02791 0.01826 0.0148 0.0734 0.9451
8.750 0.8551 0.02901 0.01937 0.0152 0.0693 0.9509
9.000 0.8742 0.03009 0.02055 0.0155 0.0655 0.9577
9.250 0.8947 0.03111 0.02167 0.0155 0.0616 0.9676
9.750 0.9327 0.03349 0.02403 0.0159 0.0564 1.0000
10.000 0.9555 0.03469 0.02543 0.0160 0.0546 1.0000
10.250 0.9781 0.03601 0.02691 0.0162 0.0526 1.0000
10.500 0.9986 0.03737 0.02840 0.0163 0.0506 1.0000
10.750 1.0171 0.03874 0.02986 0.0164 0.0487 1.0000
11.000 1.0359 0.04025 0.03141 0.0165 0.0471 1.0000
11.250 1.0573 0.04225 0.03350 0.0165 0.0459 1.0000
11.500 1.0727 0.04427 0.03583 0.0170 0.0451 1.0000
11.750 1.0846 0.04655 0.03841 0.0176 0.0442 1.0000
12.000 1.0922 0.04898 0.04114 0.0184 0.0433 1.0000
12.250 1.0959 0.05151 0.04395 0.0192 0.0424 1.0000
12.500 1.0972 0.05411 0.04681 0.0199 0.0415 1.0000
12.750 1.0960 0.05684 0.04979 0.0206 0.0407 1.0000
13.000 1.0927 0.05975 0.05291 0.0212 0.0400 1.0000
13.250 1.0871 0.06294 0.05631 0.0215 0.0395 1.0000
13.500 1.0781 0.06659 0.06018 0.0216 0.0392 1.0000
13.750 1.0659 0.07069 0.06451 0.0214 0.0390 1.0000
14.000 1.0497 0.07540 0.06945 0.0207 0.0388 1.0000
14.250 1.0286 0.08098 0.07526 0.0191 0.0387 1.0000
14.500 0.9998 0.08810 0.08265 0.0162 0.0388 1.0000
14.750 0.9528 0.09943 0.09430 0.0098 0.0392 1.0000
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Polar data table (+)
Polar graphs
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