S2050 8.93% (s2050-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2050 8.93% (s2050-il) Reynolds number: 100,000 Max Cl/Cd: 47.04 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2050-il-100000-n5.txt Download as CSV file: xf-s2050-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2050 8.93%
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5589 0.09055 0.08538 -0.0233 1.0000 0.0219
-9.750 -0.5669 0.08428 0.07917 -0.0265 1.0000 0.0219
-9.500 -0.5759 0.07785 0.07281 -0.0301 1.0000 0.0217
-9.250 -0.5870 0.07035 0.06535 -0.0351 1.0000 0.0212
-9.000 -0.6099 0.06239 0.05737 -0.0412 1.0000 0.0209
-8.750 -0.6304 0.05718 0.05207 -0.0433 1.0000 0.0204
-8.500 -0.6451 0.05189 0.04658 -0.0444 1.0000 0.0202
-8.250 -0.6531 0.04688 0.04123 -0.0446 1.0000 0.0203
-8.000 -0.6541 0.04224 0.03610 -0.0443 1.0000 0.0206
-7.750 -0.6486 0.03798 0.03133 -0.0436 1.0000 0.0209
-7.500 -0.6378 0.03426 0.02707 -0.0428 1.0000 0.0213
-7.250 -0.6227 0.03108 0.02336 -0.0418 1.0000 0.0219
-7.000 -0.6046 0.02851 0.02037 -0.0408 1.0000 0.0226
-6.750 -0.5859 0.02651 0.01822 -0.0400 1.0000 0.0237
-6.500 -0.5654 0.02496 0.01651 -0.0392 1.0000 0.0252
-6.250 -0.5439 0.02362 0.01495 -0.0383 1.0000 0.0283
-6.000 -0.5226 0.02223 0.01341 -0.0375 1.0000 0.0323
-5.750 -0.5005 0.02101 0.01207 -0.0367 1.0000 0.0375
-5.500 -0.4782 0.01988 0.01089 -0.0359 1.0000 0.0455
-5.250 -0.4552 0.01913 0.01011 -0.0354 1.0000 0.0589
-5.000 -0.4319 0.01847 0.00938 -0.0348 1.0000 0.0744
-4.750 -0.4086 0.01777 0.00862 -0.0341 1.0000 0.0889
-4.500 -0.3851 0.01710 0.00794 -0.0336 1.0000 0.1035
-4.250 -0.3616 0.01648 0.00737 -0.0330 1.0000 0.1201
-4.000 -0.3379 0.01592 0.00685 -0.0325 1.0000 0.1393
-3.750 -0.3140 0.01541 0.00640 -0.0321 1.0000 0.1641
-3.500 -0.2901 0.01490 0.00599 -0.0316 1.0000 0.1969
-3.250 -0.2662 0.01438 0.00565 -0.0313 1.0000 0.2423
-3.000 -0.2423 0.01382 0.00537 -0.0310 1.0000 0.3099
-2.750 -0.2189 0.01321 0.00518 -0.0307 1.0000 0.4064
-2.500 -0.1978 0.01272 0.00522 -0.0294 1.0000 0.5266
-2.250 -0.1782 0.01262 0.00541 -0.0275 1.0000 0.6237
-2.000 -0.1517 0.01268 0.00552 -0.0271 0.9969 0.6815
-1.750 -0.1157 0.01277 0.00562 -0.0286 0.9877 0.7254
-1.500 -0.0810 0.01283 0.00566 -0.0296 0.9778 0.7591
-1.250 -0.0468 0.01285 0.00567 -0.0305 0.9673 0.7872
-1.000 -0.0131 0.01284 0.00565 -0.0313 0.9566 0.8114
-0.750 0.0188 0.01278 0.00559 -0.0315 0.9449 0.8344
-0.500 0.0494 0.01270 0.00550 -0.0315 0.9324 0.8580
-0.250 0.0797 0.01257 0.00539 -0.0313 0.9197 0.8797
0.000 0.1123 0.01243 0.00525 -0.0316 0.9067 0.9001
0.250 0.1472 0.01229 0.00511 -0.0325 0.8928 0.9176
0.500 0.1856 0.01215 0.00496 -0.0343 0.8780 0.9322
0.750 0.2267 0.01202 0.00482 -0.0366 0.8621 0.9449
1.000 0.2702 0.01191 0.00468 -0.0394 0.8446 0.9560
1.250 0.3128 0.01182 0.00459 -0.0422 0.8235 0.9676
1.500 0.3555 0.01176 0.00448 -0.0449 0.8005 0.9790
2.000 0.4240 0.01180 0.00443 -0.0473 0.7461 1.0000
2.250 0.4508 0.01192 0.00447 -0.0470 0.7177 1.0000
2.500 0.4774 0.01207 0.00454 -0.0467 0.6884 1.0000
2.750 0.5037 0.01226 0.00464 -0.0463 0.6578 1.0000
3.000 0.5298 0.01247 0.00478 -0.0459 0.6262 1.0000
3.250 0.5555 0.01272 0.00493 -0.0454 0.5931 1.0000
3.500 0.5809 0.01299 0.00511 -0.0448 0.5585 1.0000
4.000 0.6307 0.01366 0.00559 -0.0436 0.4856 1.0000
4.250 0.6551 0.01405 0.00587 -0.0429 0.4479 1.0000
4.500 0.6793 0.01448 0.00619 -0.0422 0.4094 1.0000
4.750 0.7032 0.01495 0.00658 -0.0416 0.3702 1.0000
5.000 0.7267 0.01547 0.00698 -0.0409 0.3304 1.0000
5.250 0.7499 0.01606 0.00743 -0.0402 0.2901 1.0000
5.500 0.7729 0.01668 0.00794 -0.0396 0.2500 1.0000
5.750 0.7960 0.01735 0.00851 -0.0390 0.2128 1.0000
6.000 0.8184 0.01811 0.00918 -0.0383 0.1782 1.0000
6.250 0.8406 0.01894 0.00990 -0.0376 0.1432 1.0000
6.500 0.8618 0.01991 0.01068 -0.0369 0.1091 1.0000
6.750 0.8829 0.02092 0.01157 -0.0362 0.0829 1.0000
7.000 0.9037 0.02200 0.01264 -0.0353 0.0651 1.0000
7.250 0.9236 0.02319 0.01387 -0.0343 0.0529 1.0000
7.500 0.9425 0.02447 0.01516 -0.0332 0.0447 1.0000
7.750 0.9619 0.02573 0.01657 -0.0321 0.0398 1.0000
8.000 0.9799 0.02714 0.01806 -0.0309 0.0367 1.0000
8.250 0.9971 0.02885 0.01987 -0.0296 0.0346 1.0000
8.500 1.0163 0.03047 0.02170 -0.0284 0.0328 1.0000
8.750 1.0351 0.03205 0.02351 -0.0274 0.0306 1.0000
9.000 1.0525 0.03357 0.02515 -0.0263 0.0286 1.0000
9.250 1.0683 0.03550 0.02717 -0.0253 0.0272 1.0000
9.500 1.0835 0.03806 0.02994 -0.0241 0.0264 1.0000
9.750 1.0974 0.04056 0.03281 -0.0228 0.0258 1.0000
10.000 1.1076 0.04338 0.03601 -0.0212 0.0253 1.0000
10.250 1.1132 0.04647 0.03951 -0.0195 0.0249 1.0000
10.500 1.1135 0.04976 0.04319 -0.0175 0.0245 1.0000
10.750 1.1073 0.05300 0.04678 -0.0152 0.0243 1.0000
11.000 1.0956 0.05633 0.05042 -0.0130 0.0240 1.0000
11.250 1.0806 0.06004 0.05440 -0.0117 0.0238 1.0000
11.500 1.0626 0.06442 0.05905 -0.0119 0.0237 1.0000
11.750 1.0420 0.06978 0.06464 -0.0138 0.0237 1.0000
12.000 1.0188 0.07644 0.07152 -0.0177 0.0239 1.0000
12.250 0.9934 0.08475 0.08001 -0.0235 0.0244 1.0000
12.500 0.9656 0.09504 0.09045 -0.0311 0.0249 1.0000
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Polar data table (+)
Polar graphs
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