MA409 (original) (modified line 7) (ma409-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MA409 (original) (modified line 7) (ma409-il) Reynolds number: 100,000 Max Cl/Cd: 59.56 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ma409-il-100000-n5.txt Download as CSV file: xf-ma409-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MA409 (original)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4344 0.08634 0.08185 -0.0290 1.0000 0.0203
-8.500 -0.4380 0.08320 0.07879 -0.0291 1.0000 0.0201
-8.250 -0.4399 0.07975 0.07541 -0.0302 1.0000 0.0200
-8.000 -0.4406 0.07603 0.07175 -0.0318 1.0000 0.0198
-7.750 -0.4395 0.07194 0.06771 -0.0341 1.0000 0.0197
-7.500 -0.4360 0.06735 0.06316 -0.0372 1.0000 0.0195
-7.250 -0.4291 0.06205 0.05786 -0.0414 1.0000 0.0193
-7.000 -0.3968 0.05226 0.04789 -0.0542 0.9953 0.0191
-6.750 -0.3546 0.03769 0.03260 -0.0704 0.9900 0.0187
-6.500 -0.3149 0.02886 0.02258 -0.0786 0.9871 0.0189
-6.250 -0.2806 0.02481 0.01768 -0.0815 0.9839 0.0201
-6.000 -0.2473 0.02216 0.01454 -0.0835 0.9809 0.0230
-5.750 -0.2134 0.02044 0.01246 -0.0851 0.9784 0.0259
-5.500 -0.1806 0.01906 0.01076 -0.0862 0.9754 0.0311
-5.250 -0.1488 0.01840 0.01005 -0.0871 0.9714 0.0499
-5.000 -0.1154 0.01838 0.00973 -0.0883 0.9679 0.0779
-4.750 -0.0840 0.01814 0.00929 -0.0893 0.9641 0.0922
-4.500 -0.0543 0.01805 0.00904 -0.0900 0.9594 0.1069
-4.250 -0.0223 0.01753 0.00839 -0.0910 0.9563 0.1116
-4.000 0.0110 0.01712 0.00777 -0.0921 0.9538 0.1180
-3.750 0.0393 0.01668 0.00732 -0.0924 0.9486 0.1236
-3.500 0.0709 0.01630 0.00681 -0.0932 0.9443 0.1308
-3.250 0.1048 0.01589 0.00638 -0.0946 0.9409 0.1409
-3.000 0.1352 0.01553 0.00602 -0.0952 0.9356 0.1584
-2.750 0.1665 0.01510 0.00572 -0.0960 0.9302 0.1927
-2.500 0.2002 0.01467 0.00553 -0.0973 0.9261 0.2640
-2.250 0.2278 0.01442 0.00542 -0.0973 0.9184 0.3303
-2.000 0.2602 0.01410 0.00528 -0.0982 0.9134 0.4021
-1.750 0.2881 0.01382 0.00521 -0.0983 0.9067 0.4809
-1.500 0.3143 0.01308 0.00518 -0.0977 0.9013 0.6672
-1.250 0.3417 0.01250 0.00499 -0.0968 0.8947 1.0000
-1.000 0.3709 0.01254 0.00491 -0.0970 0.8874 1.0000
-0.750 0.4003 0.01257 0.00486 -0.0973 0.8802 1.0000
-0.500 0.4297 0.01260 0.00482 -0.0975 0.8726 1.0000
-0.250 0.4578 0.01263 0.00480 -0.0974 0.8629 1.0000
0.000 0.4876 0.01263 0.00477 -0.0976 0.8537 1.0000
0.250 0.5170 0.01264 0.00479 -0.0978 0.8445 1.0000
0.500 0.5453 0.01270 0.00486 -0.0977 0.8352 1.0000
0.750 0.5755 0.01271 0.00490 -0.0980 0.8262 1.0000
1.250 0.6377 0.01264 0.00491 -0.0985 0.8003 1.0000
1.500 0.6699 0.01260 0.00487 -0.0988 0.7812 1.0000
1.750 0.7018 0.01265 0.00494 -0.0990 0.7623 1.0000
2.000 0.7320 0.01283 0.00513 -0.0990 0.7440 1.0000
2.250 0.7587 0.01307 0.00545 -0.0985 0.7229 1.0000
2.500 0.7822 0.01330 0.00584 -0.0975 0.6938 1.0000
2.750 0.7999 0.01343 0.00566 -0.0945 0.5865 1.0000
3.000 0.8198 0.01433 0.00611 -0.0926 0.5142 1.0000
3.250 0.8394 0.01498 0.00652 -0.0910 0.4317 1.0000
3.500 0.8545 0.01614 0.00697 -0.0887 0.3095 1.0000
3.750 0.8697 0.01788 0.00775 -0.0870 0.1445 1.0000
4.000 0.8849 0.01994 0.00897 -0.0852 0.0316 1.0000
4.250 0.9066 0.02095 0.01014 -0.0840 0.0261 1.0000
4.500 0.9264 0.02224 0.01160 -0.0825 0.0216 1.0000
4.750 0.9467 0.02340 0.01298 -0.0811 0.0202 1.0000
5.000 0.9658 0.02468 0.01447 -0.0794 0.0194 1.0000
5.250 0.9840 0.02613 0.01610 -0.0777 0.0187 1.0000
5.500 1.0027 0.02770 0.01782 -0.0761 0.0175 1.0000
5.750 1.0223 0.02940 0.01965 -0.0747 0.0159 1.0000
6.000 1.0429 0.03138 0.02187 -0.0734 0.0150 1.0000
6.250 1.0646 0.03365 0.02435 -0.0722 0.0147 1.0000
6.500 1.0859 0.03618 0.02716 -0.0710 0.0145 1.0000
6.750 1.1056 0.03895 0.03028 -0.0695 0.0144 1.0000
7.000 1.1225 0.04195 0.03368 -0.0677 0.0145 1.0000
7.250 1.1359 0.04518 0.03737 -0.0656 0.0146 1.0000
7.500 1.1445 0.04872 0.04143 -0.0630 0.0149 1.0000
7.750 1.1489 0.05237 0.04555 -0.0603 0.0150 1.0000
8.000 1.1492 0.05602 0.04963 -0.0575 0.0149 1.0000
8.250 1.1453 0.05969 0.05365 -0.0547 0.0149 1.0000
8.500 1.1370 0.06332 0.05760 -0.0519 0.0148 1.0000
8.750 1.1225 0.06690 0.06146 -0.0487 0.0148 1.0000
9.000 1.1054 0.07075 0.06557 -0.0464 0.0149 1.0000
9.250 1.0859 0.07526 0.07032 -0.0454 0.0151 1.0000
9.500 1.0645 0.08076 0.07604 -0.0463 0.0155 1.0000
9.750 1.0426 0.08737 0.08285 -0.0493 0.0159 1.0000
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Polar data table (+)
Polar graphs
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