NLR-1T AIRFOIL (nlr1t-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-1T AIRFOIL (nlr1t-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.85 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlr1t-il-1000000.txt Download as CSV file: xf-nlr1t-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NLR-1T AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5554 0.08229 0.08077 -0.0214 1.0000 0.0104
-8.750 -0.5623 0.07569 0.07419 -0.0294 1.0000 0.0104
-8.500 -0.5636 0.06916 0.06759 -0.0361 0.9796 0.0105
-8.250 -0.5622 0.06360 0.06192 -0.0396 0.9644 0.0107
-8.000 -0.5612 0.05880 0.05698 -0.0407 0.9542 0.0110
-7.750 -0.5571 0.05383 0.05184 -0.0411 0.9471 0.0116
-7.500 -0.5438 0.04824 0.04596 -0.0405 0.9418 0.0125
-6.250 -0.4965 0.02847 0.02495 -0.0335 0.9249 0.0140
-6.000 -0.4764 0.02677 0.02308 -0.0326 0.9227 0.0146
-5.750 -0.4552 0.02482 0.02091 -0.0314 0.9207 0.0158
-5.500 -0.4270 0.02509 0.02097 -0.0306 0.9192 0.0171
-5.250 -0.4058 0.02339 0.01900 -0.0294 0.9175 0.0172
-5.000 -0.3916 0.01850 0.01374 -0.0275 0.9156 0.0185
-4.750 -0.3667 0.01768 0.01287 -0.0272 0.9144 0.0193
-4.500 -0.3427 0.01341 0.00803 -0.0249 0.9129 0.0142
-4.250 -0.3167 0.01249 0.00703 -0.0244 0.9118 0.0144
-4.000 -0.2904 0.01179 0.00629 -0.0241 0.9108 0.0148
-3.750 -0.2644 0.01115 0.00560 -0.0237 0.9095 0.0150
-3.500 -0.2390 0.01057 0.00497 -0.0231 0.9070 0.0153
-3.250 -0.2137 0.01006 0.00443 -0.0225 0.9045 0.0155
-3.000 -0.1879 0.00967 0.00400 -0.0220 0.9025 0.0159
-2.750 -0.1624 0.00936 0.00364 -0.0214 0.8996 0.0165
-2.500 -0.1375 0.00900 0.00324 -0.0205 0.8938 0.0168
-2.250 -0.1129 0.00871 0.00288 -0.0195 0.8855 0.0172
-2.000 -0.0888 0.00823 0.00232 -0.0184 0.8760 0.0189
-1.750 -0.0631 0.00800 0.00204 -0.0177 0.8682 0.0206
-1.500 -0.0360 0.00781 0.00185 -0.0175 0.8631 0.0226
-1.250 -0.0095 0.00752 0.00165 -0.0171 0.8594 0.0512
-1.000 0.0096 0.00632 0.00142 -0.0158 0.8556 0.3536
-0.750 0.0281 0.00533 0.00130 -0.0141 0.8516 0.6103
-0.500 0.0482 0.00479 0.00124 -0.0124 0.8465 0.7474
-0.250 0.0890 0.00446 0.00156 -0.0145 0.8415 0.9465
0.000 0.1434 0.00493 0.00201 -0.0199 0.8347 0.9777
0.250 0.1820 0.00506 0.00208 -0.0220 0.8252 0.9845
0.500 0.2208 0.00507 0.00204 -0.0244 0.8114 0.9869
0.750 0.2595 0.00510 0.00201 -0.0268 0.7895 0.9904
1.000 0.2926 0.00563 0.00196 -0.0280 0.6424 0.9941
1.250 0.3289 0.00623 0.00203 -0.0303 0.5129 0.9955
1.500 0.3635 0.00669 0.00208 -0.0322 0.4133 0.9968
1.750 0.3974 0.00708 0.00213 -0.0339 0.3346 0.9983
2.000 0.4310 0.00741 0.00219 -0.0356 0.2720 0.9996
2.250 0.4596 0.00769 0.00226 -0.0360 0.2272 1.0000
2.500 0.4851 0.00790 0.00233 -0.0357 0.1996 1.0000
2.750 0.5107 0.00805 0.00241 -0.0354 0.1834 1.0000
3.250 0.5620 0.00831 0.00256 -0.0347 0.1656 1.0000
3.500 0.5876 0.00846 0.00267 -0.0344 0.1583 1.0000
3.750 0.6133 0.00854 0.00276 -0.0340 0.1547 1.0000
4.000 0.6389 0.00867 0.00287 -0.0336 0.1500 1.0000
4.250 0.6642 0.00883 0.00299 -0.0332 0.1438 1.0000
4.500 0.6898 0.00891 0.00309 -0.0329 0.1405 1.0000
4.750 0.7152 0.00904 0.00322 -0.0325 0.1359 1.0000
5.000 0.7402 0.00922 0.00338 -0.0320 0.1299 1.0000
5.250 0.7657 0.00930 0.00348 -0.0316 0.1260 1.0000
5.500 0.7905 0.00946 0.00361 -0.0311 0.1183 1.0000
5.750 0.8154 0.00961 0.00376 -0.0306 0.1079 1.0000
6.250 0.8605 0.01054 0.00435 -0.0290 0.0542 1.0000
6.500 0.8836 0.01090 0.00468 -0.0282 0.0478 1.0000
6.750 0.9066 0.01127 0.00507 -0.0273 0.0432 1.0000
7.000 0.9303 0.01151 0.00535 -0.0266 0.0416 1.0000
7.250 0.9534 0.01181 0.00566 -0.0258 0.0394 1.0000
7.500 0.9759 0.01218 0.00604 -0.0249 0.0368 1.0000
7.750 0.9971 0.01271 0.00663 -0.0238 0.0340 1.0000
8.000 1.0198 0.01300 0.00696 -0.0230 0.0332 1.0000
8.250 1.0429 0.01322 0.00722 -0.0222 0.0324 1.0000
8.500 1.0655 0.01348 0.00751 -0.0213 0.0311 1.0000
8.750 1.0878 0.01376 0.00783 -0.0204 0.0298 1.0000
9.000 1.1095 0.01410 0.00818 -0.0195 0.0282 1.0000
9.250 1.1298 0.01458 0.00869 -0.0182 0.0263 1.0000
9.500 1.1502 0.01500 0.00917 -0.0171 0.0251 1.0000
9.750 1.1730 0.01514 0.00933 -0.0163 0.0243 1.0000
10.000 1.1951 0.01534 0.00955 -0.0154 0.0226 1.0000
10.250 1.2157 0.01568 0.00987 -0.0143 0.0196 1.0000
10.500 1.2357 0.01607 0.01021 -0.0131 0.0143 1.0000
10.750 1.2512 0.01691 0.01100 -0.0112 0.0084 1.0000
11.000 1.2675 0.01763 0.01178 -0.0094 0.0070 1.0000
11.250 1.2835 0.01831 0.01254 -0.0075 0.0063 1.0000
11.500 1.2981 0.01908 0.01339 -0.0054 0.0058 1.0000
11.750 1.3107 0.01999 0.01441 -0.0031 0.0053 1.0000
12.000 1.3222 0.02093 0.01547 -0.0005 0.0051 1.0000
12.250 1.3350 0.02168 0.01634 0.0017 0.0050 1.0000
12.500 1.3463 0.02251 0.01728 0.0042 0.0048 1.0000
12.750 1.3560 0.02341 0.01828 0.0068 0.0047 1.0000
13.000 1.3632 0.02435 0.01933 0.0098 0.0046 1.0000
13.250 1.3674 0.02534 0.02044 0.0131 0.0045 1.0000
13.500 1.3717 0.02648 0.02169 0.0161 0.0044 1.0000
13.750 1.3754 0.02776 0.02310 0.0189 0.0044 1.0000
14.000 1.3779 0.02921 0.02467 0.0214 0.0043 1.0000
14.250 1.3787 0.03086 0.02646 0.0238 0.0042 1.0000
14.500 1.3780 0.03272 0.02845 0.0259 0.0041 1.0000
14.750 1.3753 0.03487 0.03074 0.0278 0.0041 1.0000
15.000 1.3704 0.03737 0.03339 0.0293 0.0040 1.0000
15.250 1.3628 0.04035 0.03651 0.0303 0.0040 1.0000
15.500 1.3520 0.04405 0.04037 0.0304 0.0040 1.0000
15.750 1.3378 0.04884 0.04533 0.0291 0.0040 1.0000
16.000 1.3190 0.05550 0.05217 0.0254 0.0039 1.0000
16.250 1.2922 0.06528 0.06218 0.0187 0.0040 1.0000
16.500 1.2537 0.07809 0.07520 0.0108 0.0041 1.0000
16.750 1.2080 0.09099 0.08827 0.0043 0.0042 1.0000
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Polar data table (+)
Polar graphs
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