NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Reynolds number: 50,000 Max Cl/Cd: 29.82 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ms313-il-50000-n5.txt Download as CSV file: xf-ms313-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY MS(1)-0313 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5134 0.10527 0.09757 -0.0421 1.0000 0.0576
-11.250 -0.5186 0.09912 0.09145 -0.0453 1.0000 0.0574
-11.000 -0.5289 0.09224 0.08458 -0.0494 1.0000 0.0571
-10.750 -0.5446 0.08550 0.07786 -0.0536 1.0000 0.0568
-10.500 -0.5645 0.07941 0.07175 -0.0570 1.0000 0.0564
-10.250 -0.5874 0.07435 0.06665 -0.0589 1.0000 0.0561
-10.000 -0.6121 0.07047 0.06273 -0.0586 1.0000 0.0558
-9.750 -0.6341 0.06692 0.05909 -0.0575 1.0000 0.0557
-9.500 -0.6528 0.06360 0.05561 -0.0557 1.0000 0.0558
-9.250 -0.6673 0.06040 0.05218 -0.0535 1.0000 0.0561
-9.000 -0.6776 0.05727 0.04876 -0.0512 1.0000 0.0567
-8.750 -0.6836 0.05416 0.04526 -0.0490 1.0000 0.0573
-8.500 -0.6836 0.05119 0.04193 -0.0471 1.0000 0.0580
-8.250 -0.6760 0.04879 0.03940 -0.0455 1.0000 0.0589
-8.000 -0.6664 0.04650 0.03691 -0.0441 1.0000 0.0598
-7.750 -0.6547 0.04433 0.03451 -0.0427 1.0000 0.0610
-7.500 -0.6414 0.04238 0.03232 -0.0415 1.0000 0.0631
-7.250 -0.6262 0.04040 0.02998 -0.0403 1.0000 0.0658
-7.000 -0.6088 0.03845 0.02754 -0.0392 1.0000 0.0682
-6.750 -0.5906 0.03677 0.02585 -0.0381 1.0000 0.0703
-6.500 -0.5717 0.03545 0.02445 -0.0371 1.0000 0.0734
-6.250 -0.5519 0.03424 0.02303 -0.0360 1.0000 0.0778
-6.000 -0.5316 0.03304 0.02172 -0.0347 1.0000 0.0818
-5.750 -0.5118 0.03207 0.02077 -0.0335 1.0000 0.0864
-5.500 -0.4910 0.03127 0.01976 -0.0322 1.0000 0.0930
-5.250 -0.4713 0.03037 0.01897 -0.0310 1.0000 0.0995
-5.000 -0.4508 0.02961 0.01812 -0.0300 1.0000 0.1087
-4.750 -0.4301 0.02879 0.01732 -0.0293 1.0000 0.1203
-4.500 -0.4025 0.02781 0.01645 -0.0302 0.9977 0.1394
-4.250 -0.3709 0.02656 0.01553 -0.0323 0.9947 0.1782
-4.000 -0.3385 0.02449 0.01456 -0.0356 0.9924 0.3241
-3.750 -0.3223 0.02430 0.01574 -0.0317 0.9882 0.5562
-3.500 -0.2959 0.02508 0.01645 -0.0304 0.9837 0.6457
-3.250 -0.2728 0.02582 0.01706 -0.0284 0.9787 0.6939
-3.000 -0.2545 0.02669 0.01784 -0.0248 0.9736 0.7319
-2.750 -0.2369 0.02749 0.01857 -0.0207 0.9689 0.7677
-2.500 -0.2213 0.02789 0.01887 -0.0171 0.9633 0.7958
-2.250 -0.1993 0.02810 0.01895 -0.0151 0.9586 0.8164
-2.000 -0.1729 0.02820 0.01889 -0.0146 0.9542 0.8335
-1.750 -0.1516 0.02817 0.01874 -0.0134 0.9485 0.8481
-1.500 -0.1232 0.02815 0.01858 -0.0139 0.9435 0.8603
-1.250 -0.0900 0.02818 0.01846 -0.0155 0.9393 0.8699
-1.000 -0.0668 0.02811 0.01830 -0.0152 0.9327 0.8782
-0.750 -0.0352 0.02814 0.01822 -0.0167 0.9273 0.8865
-0.500 -0.0018 0.02817 0.01817 -0.0183 0.9224 0.8937
-0.250 0.0232 0.02819 0.01812 -0.0186 0.9149 0.9018
0.000 0.0579 0.02824 0.01811 -0.0205 0.9092 0.9086
0.250 0.0864 0.02832 0.01815 -0.0214 0.9018 0.9163
0.500 0.1193 0.02837 0.01818 -0.0229 0.8945 0.9233
0.750 0.1534 0.02846 0.01825 -0.0247 0.8872 0.9306
1.000 0.1862 0.02851 0.01830 -0.0261 0.8780 0.9377
1.250 0.2214 0.02856 0.01836 -0.0280 0.8688 0.9451
1.500 0.2625 0.02852 0.01836 -0.0306 0.8590 0.9514
1.750 0.2966 0.02849 0.01838 -0.0321 0.8464 0.9593
2.000 0.3397 0.02826 0.01821 -0.0347 0.8329 0.9652
2.250 0.3844 0.02779 0.01780 -0.0371 0.8166 0.9714
2.500 0.4290 0.02712 0.01721 -0.0391 0.7979 0.9772
2.750 0.4716 0.02638 0.01654 -0.0407 0.7788 0.9841
3.000 0.5130 0.02555 0.01581 -0.0419 0.7591 0.9924
3.250 0.5345 0.02509 0.01543 -0.0403 0.7359 1.0000
3.750 0.5801 0.02421 0.01472 -0.0375 0.6816 1.0000
4.000 0.6048 0.02380 0.01436 -0.0364 0.6447 1.0000
4.250 0.6303 0.02343 0.01398 -0.0353 0.5925 1.0000
4.500 0.6687 0.02278 0.01292 -0.0351 0.5077 1.0000
4.750 0.6936 0.02326 0.01270 -0.0340 0.4195 1.0000
5.000 0.7110 0.02431 0.01326 -0.0328 0.3578 1.0000
5.250 0.7294 0.02542 0.01403 -0.0321 0.3152 1.0000
5.500 0.7498 0.02649 0.01483 -0.0317 0.2843 1.0000
5.750 0.7726 0.02749 0.01568 -0.0317 0.2610 1.0000
6.000 0.7973 0.02847 0.01656 -0.0318 0.2436 1.0000
6.250 0.8236 0.02943 0.01743 -0.0322 0.2289 1.0000
6.500 0.8512 0.03038 0.01830 -0.0327 0.2165 1.0000
6.750 0.8808 0.03133 0.01920 -0.0335 0.2062 1.0000
7.000 0.9132 0.03230 0.02025 -0.0345 0.1975 1.0000
7.250 0.9446 0.03332 0.02119 -0.0355 0.1901 1.0000
7.500 0.9747 0.03441 0.02243 -0.0362 0.1825 1.0000
7.750 1.0040 0.03552 0.02355 -0.0369 0.1761 1.0000
8.000 1.0347 0.03681 0.02489 -0.0378 0.1713 1.0000
8.250 1.0623 0.03820 0.02653 -0.0383 0.1664 1.0000
8.500 1.0888 0.03955 0.02797 -0.0387 0.1617 1.0000
8.750 1.1166 0.04098 0.02934 -0.0393 0.1575 1.0000
9.000 1.1369 0.04270 0.03146 -0.0389 0.1532 1.0000
9.250 1.1586 0.04451 0.03354 -0.0387 0.1498 1.0000
9.500 1.1803 0.04622 0.03541 -0.0385 0.1464 1.0000
9.750 1.2047 0.04787 0.03704 -0.0387 0.1432 1.0000
10.000 1.2148 0.05020 0.03983 -0.0373 0.1400 1.0000
10.250 1.2239 0.05264 0.04266 -0.0359 0.1369 1.0000
10.500 1.2333 0.05505 0.04537 -0.0347 0.1342 1.0000
10.750 1.2444 0.05721 0.04771 -0.0336 0.1315 1.0000
11.000 1.2633 0.05901 0.04952 -0.0333 0.1287 1.0000
11.250 1.2550 0.06224 0.05315 -0.0307 0.1267 1.0000
11.500 1.2351 0.06580 0.05711 -0.0273 0.1251 1.0000
11.750 1.2114 0.06986 0.06152 -0.0245 0.1238 1.0000
12.000 1.1819 0.07479 0.06677 -0.0227 0.1229 1.0000
12.250 1.1425 0.08133 0.07360 -0.0226 0.1224 1.0000
12.500 1.0810 0.09191 0.08445 -0.0259 0.1227 1.0000
12.750 0.9756 0.11519 0.10786 -0.0402 0.1235 1.0000
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Polar data table (+)
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