NACA M22 AIRFOIL (m22-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: NACA M22 AIRFOIL (m22-il) Reynolds number: 50,000 Max Cl/Cd: 32.78 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m22-il-50000-n5.txt Download as CSV file: xf-m22-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M22 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3554 0.11877 0.11356 -0.0004 0.9102 0.0437
-8.250 -0.3512 0.11752 0.11227 -0.0035 0.8887 0.0441
-8.000 -0.3464 0.11636 0.11107 -0.0067 0.8724 0.0443
-7.750 -0.3379 0.11502 0.10967 -0.0105 0.8585 0.0444
-7.500 -0.3298 0.10846 0.10313 -0.0086 0.8481 0.0451
-7.250 -0.3227 0.10285 0.09748 -0.0061 0.8383 0.0470
-7.000 -0.3132 0.09952 0.09411 -0.0072 0.8278 0.0494
-6.750 -0.3024 0.09669 0.09123 -0.0093 0.8180 0.0522
-6.500 -0.2896 0.09454 0.08900 -0.0126 0.8090 0.0554
-6.250 -0.2676 0.09426 0.08859 -0.0197 0.7991 0.0572
-6.000 -0.2476 0.09228 0.08651 -0.0241 0.7907 0.0578
-5.750 -0.2440 0.08543 0.07968 -0.0208 0.7836 0.0596
-5.500 -0.2303 0.08176 0.07595 -0.0217 0.7757 0.0624
-5.250 -0.2127 0.07889 0.07298 -0.0238 0.7683 0.0662
-5.000 -0.1758 0.07917 0.07293 -0.0314 0.7599 0.0709
-4.750 -0.1688 0.07338 0.06722 -0.0298 0.7537 0.0733
-4.500 -0.1505 0.07013 0.06388 -0.0310 0.7462 0.0799
-4.250 -0.1156 0.06941 0.06282 -0.0360 0.7392 0.0853
-4.000 -0.1039 0.06448 0.05792 -0.0353 0.7325 0.0889
-3.750 -0.0744 0.06290 0.05604 -0.0380 0.7257 0.0976
-3.500 -0.0552 0.05925 0.05232 -0.0386 0.7195 0.1027
-3.000 -0.0066 0.05444 0.04712 -0.0409 0.7069 0.1233
-2.750 0.0208 0.05209 0.04457 -0.0426 0.6997 0.1314
-2.250 0.0710 0.04779 0.03985 -0.0441 0.6871 0.1604
-1.500 0.1410 0.04175 0.03329 -0.0449 0.6690 0.2454
-1.000 0.2240 0.03977 0.03017 -0.0474 0.6568 0.1097
-0.750 0.2538 0.03822 0.02823 -0.0472 0.6520 0.0945
-0.500 0.2842 0.03741 0.02708 -0.0477 0.6453 0.0974
-0.250 0.3115 0.03611 0.02556 -0.0477 0.6396 0.0946
0.000 0.3403 0.03498 0.02407 -0.0475 0.6350 0.0890
0.250 0.3718 0.03440 0.02308 -0.0480 0.6279 0.0841
0.500 0.3993 0.03341 0.02187 -0.0477 0.6232 0.0824
0.750 0.4281 0.03283 0.02111 -0.0483 0.6167 0.0808
1.000 0.4590 0.03226 0.02025 -0.0486 0.6111 0.0794
1.250 0.4915 0.03163 0.01927 -0.0489 0.6068 0.0784
1.500 0.5244 0.03146 0.01894 -0.0504 0.5992 0.0779
1.750 0.5544 0.03100 0.01826 -0.0503 0.5947 0.0780
2.000 0.5825 0.03093 0.01807 -0.0507 0.5885 0.0788
2.250 0.6082 0.03082 0.01785 -0.0505 0.5828 0.0802
2.500 0.6324 0.03053 0.01739 -0.0493 0.5790 0.0825
2.750 0.6562 0.03097 0.01786 -0.0497 0.5717 0.0861
3.000 0.6799 0.03104 0.01789 -0.0491 0.5670 0.0986
3.250 0.7033 0.03115 0.01807 -0.0485 0.5623 0.1178
3.500 0.7260 0.03168 0.01875 -0.0487 0.5554 0.1472
3.750 0.7837 0.03044 0.01872 -0.0545 0.5510 1.0000
4.000 0.8059 0.03148 0.01971 -0.0548 0.5442 1.0000
4.250 0.8285 0.03211 0.02030 -0.0543 0.5389 1.0000
4.500 0.8522 0.03236 0.02049 -0.0533 0.5356 1.0000
4.750 0.8713 0.03392 0.02221 -0.0539 0.5274 1.0000
5.000 0.8940 0.03443 0.02275 -0.0532 0.5231 1.0000
5.250 0.9141 0.03552 0.02393 -0.0530 0.5175 1.0000
5.500 0.9329 0.03679 0.02534 -0.0529 0.5110 1.0000
5.750 0.9562 0.03716 0.02584 -0.0520 0.5075 1.0000
6.000 0.9691 0.03936 0.02824 -0.0524 0.4993 1.0000
6.250 0.9897 0.04017 0.02921 -0.0517 0.4948 1.0000
6.500 1.0142 0.04039 0.02959 -0.0506 0.4919 1.0000
6.750 1.0181 0.04364 0.03308 -0.0512 0.4819 1.0000
7.000 1.0550 0.03977 0.02939 -0.0473 0.4660 1.0000
7.250 1.0840 0.03683 0.02660 -0.0439 0.4440 1.0000
7.500 1.1082 0.03468 0.02460 -0.0410 0.4159 1.0000
7.750 1.1235 0.03427 0.02437 -0.0392 0.3805 1.0000
8.000 1.1318 0.03500 0.02521 -0.0377 0.3275 1.0000
8.250 1.1220 0.03723 0.02618 -0.0352 0.1746 1.0000
8.500 1.1001 0.04178 0.03021 -0.0343 0.0967 1.0000
8.750 1.0800 0.04651 0.03461 -0.0337 0.0698 1.0000
9.000 1.0682 0.05063 0.03865 -0.0334 0.0550 1.0000
9.500 1.0553 0.05805 0.04618 -0.0329 0.0452 1.0000
9.750 1.0506 0.06166 0.04993 -0.0328 0.0430 1.0000
10.000 1.0455 0.06537 0.05377 -0.0328 0.0413 1.0000
10.250 1.0399 0.06921 0.05772 -0.0328 0.0399 1.0000
10.500 1.0340 0.07309 0.06169 -0.0329 0.0389 1.0000
10.750 1.0313 0.07658 0.06535 -0.0329 0.0377 1.0000
11.000 1.0292 0.08004 0.06895 -0.0329 0.0362 1.0000
11.250 1.0279 0.08340 0.07244 -0.0329 0.0346 1.0000
11.500 1.0272 0.08662 0.07574 -0.0327 0.0330 1.0000
11.750 1.0274 0.08958 0.07874 -0.0323 0.0317 1.0000
12.000 1.0315 0.09171 0.08088 -0.0312 0.0307 1.0000
12.250 1.0434 0.09270 0.08203 -0.0291 0.0301 1.0000
12.500 1.0630 0.09246 0.08205 -0.0258 0.0295 1.0000
12.750 1.0928 0.09117 0.08103 -0.0213 0.0284 1.0000
13.000 1.1226 0.09089 0.08107 -0.0174 0.0265 1.0000
13.250 1.1453 0.09231 0.08279 -0.0148 0.0255 1.0000
13.500 1.1574 0.09523 0.08603 -0.0136 0.0254 1.0000
13.750 1.1597 0.09917 0.09028 -0.0136 0.0255 1.0000
14.000 1.1560 0.10371 0.09511 -0.0144 0.0256 1.0000
14.250 1.1486 0.10869 0.10036 -0.0158 0.0258 1.0000
14.500 1.1389 0.11414 0.10606 -0.0178 0.0260 1.0000
14.750 1.1276 0.12003 0.11217 -0.0204 0.0262 1.0000
15.000 1.1152 0.12636 0.11872 -0.0235 0.0264 1.0000
15.250 1.1023 0.13314 0.12568 -0.0272 0.0266 1.0000
15.500 1.0893 0.14038 0.13309 -0.0314 0.0269 1.0000
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Polar data table (+)
Polar graphs
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