NACA-0009 9.0% smoothed (n0009sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA-0009 9.0% smoothed (n0009sm-il) Reynolds number: 200,000 Max Cl/Cd: 42.19 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n0009sm-il-200000-n5.txt Download as CSV file: xf-n0009sm-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA-0009 9.0% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8683 0.08119 0.07741 -0.0163 1.0000 0.0108
-13.000 -0.8961 0.07048 0.06658 -0.0237 1.0000 0.0104
-12.750 -0.9234 0.06071 0.05661 -0.0312 1.0000 0.0104
-12.500 -0.9444 0.05377 0.04947 -0.0361 1.0000 0.0103
-12.250 -0.9627 0.04855 0.04402 -0.0386 1.0000 0.0103
-12.000 -0.9796 0.04441 0.03962 -0.0389 1.0000 0.0104
-11.750 -0.9928 0.04121 0.03618 -0.0374 1.0000 0.0106
-11.500 -1.0025 0.03860 0.03331 -0.0348 1.0000 0.0107
-11.250 -1.0091 0.03638 0.03083 -0.0315 1.0000 0.0110
-11.000 -1.0133 0.03413 0.02839 -0.0283 1.0000 0.0113
-10.750 -1.0086 0.03249 0.02660 -0.0259 1.0000 0.0119
-10.500 -0.9987 0.03124 0.02522 -0.0240 1.0000 0.0126
-10.250 -0.9853 0.03030 0.02410 -0.0223 1.0000 0.0138
-10.000 -0.9732 0.02889 0.02245 -0.0204 1.0000 0.0152
-9.750 -0.9609 0.02734 0.02065 -0.0184 1.0000 0.0164
-9.500 -0.9475 0.02615 0.01937 -0.0166 1.0000 0.0178
-9.250 -0.9308 0.02528 0.01838 -0.0150 1.0000 0.0193
-9.000 -0.9129 0.02446 0.01739 -0.0136 1.0000 0.0217
-8.750 -0.8963 0.02334 0.01610 -0.0119 1.0000 0.0239
-8.500 -0.8783 0.02264 0.01534 -0.0105 1.0000 0.0262
-8.250 -0.8593 0.02190 0.01449 -0.0091 1.0000 0.0286
-8.000 -0.8392 0.02128 0.01364 -0.0077 1.0000 0.0314
-7.750 -0.8212 0.02038 0.01269 -0.0062 1.0000 0.0342
-7.500 -0.8009 0.01989 0.01214 -0.0050 1.0000 0.0372
-7.250 -0.7803 0.01935 0.01149 -0.0037 1.0000 0.0406
-7.000 -0.7593 0.01881 0.01079 -0.0024 1.0000 0.0428
-6.750 -0.7413 0.01792 0.00991 -0.0008 1.0000 0.0461
-6.500 -0.7209 0.01738 0.00932 0.0005 1.0000 0.0493
-6.250 -0.7005 0.01682 0.00865 0.0019 1.0000 0.0522
-6.000 -0.6798 0.01632 0.00804 0.0033 1.0000 0.0547
-5.750 -0.6608 0.01566 0.00740 0.0048 1.0000 0.0589
-5.500 -0.6401 0.01522 0.00692 0.0062 1.0000 0.0635
-5.250 -0.6191 0.01482 0.00643 0.0075 1.0000 0.0677
-5.000 -0.5992 0.01429 0.00593 0.0090 1.0000 0.0733
-4.750 -0.5782 0.01392 0.00549 0.0103 1.0000 0.0802
-4.500 -0.5577 0.01349 0.00511 0.0116 1.0000 0.0902
-4.250 -0.5371 0.01309 0.00476 0.0130 1.0000 0.1048
-4.000 -0.5168 0.01267 0.00444 0.0143 1.0000 0.1273
-3.750 -0.4966 0.01226 0.00417 0.0157 1.0000 0.1592
-3.500 -0.4767 0.01185 0.00391 0.0170 1.0000 0.2008
-3.250 -0.4571 0.01143 0.00372 0.0184 1.0000 0.2512
-3.000 -0.4375 0.01107 0.00358 0.0199 1.0000 0.3042
-2.750 -0.4035 0.01071 0.00345 0.0182 0.9952 0.3638
-2.500 -0.3702 0.01033 0.00332 0.0168 0.9893 0.4283
-2.250 -0.3362 0.01000 0.00324 0.0153 0.9832 0.4910
-2.000 -0.3050 0.00964 0.00317 0.0146 0.9760 0.5579
-1.750 -0.2727 0.00927 0.00313 0.0137 0.9693 0.6371
-1.500 -0.2427 0.00898 0.00310 0.0136 0.9608 0.6983
-1.250 -0.2066 0.00878 0.00307 0.0122 0.9547 0.7463
-1.000 -0.1741 0.00861 0.00306 0.0116 0.9452 0.7892
-0.750 -0.1346 0.00852 0.00306 0.0096 0.9377 0.8287
-0.500 -0.0920 0.00849 0.00311 0.0069 0.9290 0.8619
-0.250 -0.0473 0.00849 0.00314 0.0037 0.9187 0.8872
0.000 0.0000 0.00850 0.00316 0.0000 0.9055 0.9055
0.250 0.0472 0.00850 0.00315 -0.0037 0.8874 0.9187
0.500 0.0920 0.00849 0.00311 -0.0069 0.8619 0.9290
0.750 0.1347 0.00852 0.00306 -0.0096 0.8286 0.9378
1.000 0.1741 0.00861 0.00306 -0.0116 0.7890 0.9452
1.250 0.2066 0.00878 0.00307 -0.0122 0.7458 0.9547
1.500 0.2427 0.00898 0.00310 -0.0136 0.6986 0.9608
1.750 0.2727 0.00926 0.00313 -0.0137 0.6371 0.9693
2.000 0.3049 0.00964 0.00316 -0.0145 0.5577 0.9760
2.250 0.3361 0.01000 0.00324 -0.0153 0.4906 0.9833
2.500 0.3703 0.01033 0.00332 -0.0168 0.4285 0.9894
2.750 0.4037 0.01070 0.00345 -0.0182 0.3647 0.9953
3.000 0.4374 0.01107 0.00358 -0.0198 0.3041 1.0000
3.250 0.4570 0.01143 0.00372 -0.0184 0.2518 1.0000
3.500 0.4766 0.01185 0.00391 -0.0170 0.2001 1.0000
3.750 0.4965 0.01226 0.00416 -0.0156 0.1592 1.0000
4.000 0.5167 0.01267 0.00444 -0.0143 0.1270 1.0000
4.250 0.5370 0.01309 0.00476 -0.0129 0.1048 1.0000
4.500 0.5576 0.01349 0.00511 -0.0116 0.0900 1.0000
4.750 0.5781 0.01392 0.00549 -0.0103 0.0799 1.0000
5.000 0.5991 0.01429 0.00591 -0.0089 0.0732 1.0000
5.250 0.6189 0.01482 0.00643 -0.0075 0.0677 1.0000
5.500 0.6400 0.01522 0.00692 -0.0061 0.0636 1.0000
5.750 0.6607 0.01566 0.00740 -0.0048 0.0589 1.0000
6.000 0.6797 0.01633 0.00804 -0.0033 0.0547 1.0000
6.250 0.7004 0.01682 0.00865 -0.0019 0.0523 1.0000
6.500 0.7208 0.01738 0.00932 -0.0005 0.0493 1.0000
6.750 0.7412 0.01792 0.00992 0.0008 0.0461 1.0000
7.000 0.7593 0.01882 0.01080 0.0024 0.0428 1.0000
7.250 0.7803 0.01935 0.01149 0.0037 0.0405 1.0000
7.500 0.8009 0.01989 0.01215 0.0050 0.0373 1.0000
7.750 0.8212 0.02038 0.01269 0.0062 0.0342 1.0000
8.000 0.8391 0.02130 0.01367 0.0078 0.0314 1.0000
8.250 0.8593 0.02192 0.01450 0.0091 0.0287 1.0000
8.500 0.8784 0.02263 0.01534 0.0105 0.0262 1.0000
8.750 0.8963 0.02337 0.01613 0.0119 0.0239 1.0000
9.000 0.9134 0.02439 0.01732 0.0135 0.0216 1.0000
9.250 0.9310 0.02527 0.01837 0.0150 0.0193 1.0000
9.500 0.9476 0.02616 0.01938 0.0166 0.0178 1.0000
9.750 0.9610 0.02736 0.02066 0.0184 0.0164 1.0000
10.000 0.9737 0.02884 0.02240 0.0203 0.0151 1.0000
10.250 0.9860 0.03024 0.02403 0.0222 0.0138 1.0000
10.500 0.9974 0.03150 0.02550 0.0241 0.0128 1.0000
10.750 1.0093 0.03244 0.02654 0.0258 0.0118 1.0000
11.000 1.0136 0.03415 0.02841 0.0282 0.0113 1.0000
11.250 1.0101 0.03635 0.03079 0.0314 0.0110 1.0000
11.500 1.0030 0.03862 0.03333 0.0347 0.0107 1.0000
11.750 0.9925 0.04132 0.03630 0.0374 0.0105 1.0000
12.000 0.9801 0.04445 0.03968 0.0388 0.0103 1.0000
12.250 0.9643 0.04846 0.04392 0.0385 0.0103 1.0000
12.500 0.9459 0.05369 0.04938 0.0360 0.0103 1.0000
12.750 0.9253 0.06053 0.05641 0.0312 0.0104 1.0000
13.000 0.9002 0.06982 0.06590 0.0240 0.0105 1.0000
13.250 0.8717 0.08063 0.07683 0.0165 0.0108 1.0000
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Polar data table (+)
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