NACA M3 (nacam3-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M3 (nacam3-il) Reynolds number: 100,000 Max Cl/Cd: 34.58 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam3-il-100000-n5.txt Download as CSV file: xf-nacam3-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M3
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7833 0.10665 0.10104 -0.0110 1.0000 0.0438
-13.250 -0.8415 0.08888 0.08315 -0.0233 1.0000 0.0430
-13.000 -0.8843 0.07759 0.07165 -0.0313 1.0000 0.0425
-12.750 -0.9174 0.06981 0.06363 -0.0358 1.0000 0.0423
-12.500 -0.9446 0.06400 0.05756 -0.0378 1.0000 0.0423
-12.250 -0.9671 0.05944 0.05272 -0.0379 1.0000 0.0425
-12.000 -0.9860 0.05569 0.04869 -0.0365 1.0000 0.0427
-11.750 -1.0012 0.05252 0.04521 -0.0339 1.0000 0.0431
-11.500 -1.0124 0.04970 0.04207 -0.0308 1.0000 0.0434
-11.250 -1.0172 0.04696 0.03893 -0.0281 1.0000 0.0440
-11.000 -1.0144 0.04452 0.03621 -0.0260 1.0000 0.0448
-10.750 -1.0024 0.04274 0.03439 -0.0248 1.0000 0.0458
-10.500 -0.9908 0.04112 0.03263 -0.0233 1.0000 0.0469
-10.250 -0.9784 0.03939 0.03071 -0.0218 1.0000 0.0479
-10.000 -0.9646 0.03758 0.02866 -0.0203 1.0000 0.0489
-9.750 -0.9492 0.03583 0.02667 -0.0190 1.0000 0.0500
-9.500 -0.9326 0.03429 0.02488 -0.0176 1.0000 0.0514
-9.250 -0.9150 0.03289 0.02320 -0.0163 1.0000 0.0528
-9.000 -0.8958 0.03140 0.02171 -0.0154 1.0000 0.0542
-8.750 -0.8765 0.03018 0.02044 -0.0144 1.0000 0.0554
-8.500 -0.8571 0.02904 0.01923 -0.0132 1.0000 0.0568
-8.250 -0.8377 0.02795 0.01806 -0.0120 1.0000 0.0583
-8.000 -0.8184 0.02695 0.01697 -0.0108 1.0000 0.0602
-7.750 -0.7989 0.02607 0.01593 -0.0094 1.0000 0.0625
-7.500 -0.7816 0.02507 0.01497 -0.0079 1.0000 0.0648
-7.250 -0.7639 0.02422 0.01413 -0.0064 1.0000 0.0673
-7.000 -0.7463 0.02342 0.01328 -0.0047 1.0000 0.0702
-6.750 -0.7285 0.02268 0.01244 -0.0030 1.0000 0.0735
-6.500 -0.7123 0.02184 0.01165 -0.0011 1.0000 0.0776
-6.250 -0.6947 0.02115 0.01093 0.0006 1.0000 0.0842
-6.000 -0.6777 0.02041 0.01026 0.0023 1.0000 0.0934
-5.750 -0.6603 0.01970 0.00962 0.0040 1.0000 0.1071
-5.500 -0.6426 0.01903 0.00903 0.0056 1.0000 0.1271
-5.250 -0.6249 0.01837 0.00852 0.0072 1.0000 0.1534
-5.000 -0.6067 0.01777 0.00807 0.0087 1.0000 0.1861
-4.750 -0.5887 0.01718 0.00768 0.0102 1.0000 0.2268
-4.500 -0.5705 0.01662 0.00736 0.0116 1.0000 0.2745
-4.250 -0.5529 0.01603 0.00711 0.0132 1.0000 0.3376
-4.000 -0.5354 0.01548 0.00694 0.0149 1.0000 0.4065
-3.750 -0.5167 0.01507 0.00681 0.0165 1.0000 0.4667
-3.500 -0.4968 0.01478 0.00672 0.0179 1.0000 0.5160
-3.250 -0.4761 0.01458 0.00668 0.0193 1.0000 0.5599
-3.000 -0.4552 0.01443 0.00669 0.0207 1.0000 0.6054
-2.750 -0.4202 0.01434 0.00675 0.0193 0.9945 0.6553
-2.500 -0.3847 0.01429 0.00681 0.0180 0.9879 0.6970
-2.250 -0.3478 0.01431 0.00687 0.0164 0.9817 0.7323
-2.000 -0.3117 0.01435 0.00696 0.0151 0.9746 0.7633
-1.750 -0.2752 0.01442 0.00706 0.0137 0.9676 0.7907
-1.500 -0.2373 0.01449 0.00713 0.0120 0.9606 0.8155
-1.250 -0.1995 0.01458 0.00722 0.0104 0.9531 0.8354
-1.000 -0.1585 0.01466 0.00729 0.0080 0.9462 0.8533
-0.750 -0.1204 0.01472 0.00734 0.0063 0.9376 0.8694
-0.500 -0.0792 0.01476 0.00737 0.0040 0.9297 0.8839
-0.250 -0.0418 0.01480 0.00740 0.0024 0.9190 0.8978
0.000 0.0000 0.01480 0.00740 0.0000 0.9097 0.9097
0.250 0.0418 0.01479 0.00740 -0.0024 0.8978 0.9190
0.500 0.0792 0.01476 0.00737 -0.0040 0.8839 0.9297
0.750 0.1204 0.01472 0.00734 -0.0063 0.8694 0.9376
1.000 0.1585 0.01466 0.00729 -0.0080 0.8533 0.9463
1.250 0.1995 0.01458 0.00722 -0.0104 0.8354 0.9531
1.500 0.2373 0.01449 0.00713 -0.0120 0.8155 0.9606
1.750 0.2752 0.01442 0.00706 -0.0137 0.7907 0.9676
2.000 0.3117 0.01435 0.00696 -0.0151 0.7634 0.9746
2.250 0.3478 0.01431 0.00687 -0.0164 0.7323 0.9817
2.500 0.3847 0.01429 0.00681 -0.0180 0.6970 0.9879
2.750 0.4202 0.01433 0.00675 -0.0193 0.6553 0.9945
3.000 0.4551 0.01443 0.00668 -0.0207 0.6055 1.0000
3.250 0.4760 0.01458 0.00668 -0.0193 0.5600 1.0000
3.500 0.4967 0.01478 0.00672 -0.0179 0.5161 1.0000
3.750 0.5166 0.01507 0.00680 -0.0164 0.4668 1.0000
4.000 0.5353 0.01548 0.00693 -0.0148 0.4066 1.0000
4.250 0.5529 0.01602 0.00711 -0.0132 0.3377 1.0000
4.500 0.5704 0.01662 0.00736 -0.0116 0.2745 1.0000
4.750 0.5886 0.01717 0.00768 -0.0102 0.2269 1.0000
5.000 0.6066 0.01777 0.00807 -0.0087 0.1862 1.0000
5.250 0.6248 0.01837 0.00851 -0.0072 0.1534 1.0000
5.500 0.6425 0.01902 0.00902 -0.0056 0.1272 1.0000
5.750 0.6603 0.01969 0.00961 -0.0040 0.1071 1.0000
6.000 0.6776 0.02041 0.01025 -0.0023 0.0934 1.0000
6.250 0.6946 0.02115 0.01093 -0.0006 0.0842 1.0000
6.500 0.7122 0.02184 0.01164 0.0011 0.0776 1.0000
6.750 0.7285 0.02268 0.01244 0.0030 0.0735 1.0000
7.000 0.7462 0.02342 0.01328 0.0047 0.0702 1.0000
7.250 0.7639 0.02422 0.01412 0.0064 0.0673 1.0000
7.500 0.7816 0.02506 0.01497 0.0079 0.0648 1.0000
7.750 0.7989 0.02607 0.01593 0.0094 0.0625 1.0000
8.000 0.8184 0.02695 0.01697 0.0108 0.0602 1.0000
8.250 0.8378 0.02795 0.01806 0.0120 0.0583 1.0000
8.500 0.8572 0.02903 0.01923 0.0132 0.0568 1.0000
8.750 0.8766 0.03018 0.02044 0.0143 0.0554 1.0000
9.000 0.8959 0.03140 0.02171 0.0154 0.0542 1.0000
9.250 0.9151 0.03289 0.02320 0.0163 0.0528 1.0000
9.500 0.9327 0.03429 0.02489 0.0176 0.0514 1.0000
9.750 0.9493 0.03583 0.02668 0.0189 0.0500 1.0000
10.000 0.9648 0.03758 0.02866 0.0203 0.0489 1.0000
10.250 0.9787 0.03939 0.03071 0.0217 0.0479 1.0000
10.500 0.9911 0.04112 0.03264 0.0232 0.0469 1.0000
10.750 1.0028 0.04275 0.03439 0.0247 0.0458 1.0000
11.000 1.0148 0.04453 0.03622 0.0259 0.0448 1.0000
11.250 1.0175 0.04697 0.03895 0.0281 0.0440 1.0000
11.500 1.0127 0.04972 0.04209 0.0307 0.0434 1.0000
11.750 1.0017 0.05254 0.04524 0.0338 0.0431 1.0000
12.000 0.9864 0.05573 0.04873 0.0364 0.0427 1.0000
12.250 0.9676 0.05948 0.05277 0.0377 0.0424 1.0000
12.500 0.9451 0.06406 0.05762 0.0376 0.0423 1.0000
12.750 0.9180 0.06989 0.06371 0.0356 0.0423 1.0000
13.000 0.8846 0.07774 0.07180 0.0310 0.0425 1.0000
13.250 0.8416 0.08915 0.08342 0.0228 0.0430 1.0000
13.500 0.7831 0.10709 0.10149 0.0105 0.0438 1.0000
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Polar data table (+)
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