NLR-1T AIRFOIL (nlr1t-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLR-1T AIRFOIL (nlr1t-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.91 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlr1t-il-1000000-n5.txt Download as CSV file: xf-nlr1t-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5794 0.08429 0.08265 -0.0188 0.9420 0.0059
-9.250 -0.5898 0.07749 0.07582 -0.0246 0.9288 0.0060
-8.750 -0.6178 0.06299 0.06109 -0.0350 0.9116 0.0060
-8.500 -0.6288 0.05498 0.05286 -0.0367 0.9063 0.0062
-8.250 -0.6400 0.04554 0.04307 -0.0361 0.9021 0.0065
-8.000 -0.6465 0.03608 0.03316 -0.0337 0.8984 0.0067
-7.750 -0.6512 0.02743 0.02383 -0.0299 0.8949 0.0068
-7.500 -0.6493 0.02145 0.01711 -0.0265 0.8921 0.0070
-7.250 -0.6288 0.02003 0.01549 -0.0256 0.8905 0.0072
-7.000 -0.6059 0.01911 0.01444 -0.0250 0.8890 0.0074
-6.750 -0.5825 0.01814 0.01333 -0.0244 0.8874 0.0075
-6.500 -0.5593 0.01691 0.01191 -0.0236 0.8858 0.0076
-6.250 -0.5352 0.01592 0.01077 -0.0231 0.8842 0.0078
-6.000 -0.5104 0.01504 0.00977 -0.0225 0.8829 0.0080
-5.750 -0.4852 0.01427 0.00889 -0.0221 0.8816 0.0082
-5.500 -0.4599 0.01354 0.00806 -0.0216 0.8804 0.0085
-5.250 -0.4342 0.01291 0.00733 -0.0212 0.8792 0.0088
-5.000 -0.4084 0.01234 0.00668 -0.0209 0.8781 0.0090
-4.750 -0.3825 0.01181 0.00608 -0.0205 0.8770 0.0093
-4.500 -0.3565 0.01134 0.00556 -0.0201 0.8760 0.0095
-4.250 -0.3304 0.01091 0.00508 -0.0198 0.8750 0.0097
-4.000 -0.3041 0.01051 0.00463 -0.0195 0.8734 0.0098
-3.750 -0.2779 0.01013 0.00423 -0.0191 0.8708 0.0100
-3.500 -0.2515 0.00980 0.00387 -0.0188 0.8684 0.0101
-3.250 -0.2246 0.00956 0.00361 -0.0187 0.8670 0.0102
-3.000 -0.1993 0.00903 0.00303 -0.0181 0.8658 0.0107
-2.750 -0.1729 0.00872 0.00267 -0.0178 0.8635 0.0111
-2.500 -0.1465 0.00846 0.00239 -0.0174 0.8582 0.0115
-2.250 -0.1204 0.00824 0.00212 -0.0169 0.8480 0.0121
-2.000 -0.0943 0.00805 0.00187 -0.0163 0.8328 0.0128
-1.750 -0.0677 0.00790 0.00167 -0.0160 0.8173 0.0135
-1.500 -0.0405 0.00778 0.00151 -0.0158 0.8053 0.0142
-1.250 -0.0130 0.00766 0.00139 -0.0156 0.7968 0.0149
-1.000 0.0143 0.00755 0.00126 -0.0155 0.7828 0.0177
-0.750 0.0370 0.00765 0.00110 -0.0143 0.6848 0.0419
-0.500 0.0584 0.00757 0.00108 -0.0132 0.6089 0.1526
-0.250 0.0786 0.00719 0.00104 -0.0120 0.5452 0.3406
0.000 0.0931 0.00629 0.00100 -0.0098 0.4930 0.6487
0.250 0.1071 0.00578 0.00102 -0.0067 0.4456 0.8372
0.750 0.1791 0.00645 0.00156 -0.0101 0.3363 0.9666
1.000 0.2119 0.00678 0.00171 -0.0112 0.2950 0.9749
1.250 0.2509 0.00708 0.00182 -0.0139 0.2555 0.9774
1.500 0.2842 0.00732 0.00191 -0.0153 0.2228 0.9797
1.750 0.3140 0.00751 0.00198 -0.0159 0.2003 0.9820
2.000 0.3395 0.00767 0.00206 -0.0154 0.1866 0.9848
2.250 0.3726 0.00780 0.00213 -0.0167 0.1756 0.9856
2.500 0.4052 0.00793 0.00220 -0.0179 0.1671 0.9864
2.750 0.4370 0.00807 0.00228 -0.0189 0.1579 0.9872
3.000 0.4680 0.00820 0.00236 -0.0198 0.1494 0.9881
3.250 0.4984 0.00835 0.00246 -0.0205 0.1421 0.9891
3.500 0.5290 0.00846 0.00255 -0.0212 0.1388 0.9902
3.750 0.5596 0.00858 0.00265 -0.0219 0.1342 0.9915
4.000 0.5898 0.00873 0.00278 -0.0226 0.1295 0.9928
4.250 0.6196 0.00886 0.00290 -0.0232 0.1253 0.9942
4.500 0.6518 0.00898 0.00301 -0.0243 0.1202 0.9950
4.750 0.6838 0.00914 0.00313 -0.0254 0.1133 0.9958
5.000 0.7158 0.00928 0.00326 -0.0265 0.1046 0.9967
5.250 0.7472 0.00958 0.00343 -0.0277 0.0817 0.9978
5.500 0.7785 0.01000 0.00371 -0.0288 0.0578 0.9989
5.750 0.8104 0.01032 0.00397 -0.0300 0.0473 0.9999
6.000 0.8353 0.01059 0.00423 -0.0296 0.0419 1.0000
6.250 0.8595 0.01080 0.00446 -0.0289 0.0394 1.0000
6.500 0.8833 0.01105 0.00470 -0.0283 0.0365 1.0000
6.750 0.9067 0.01133 0.00498 -0.0276 0.0335 1.0000
7.000 0.9300 0.01163 0.00529 -0.0268 0.0307 1.0000
7.250 0.9535 0.01186 0.00556 -0.0261 0.0299 1.0000
7.500 0.9769 0.01210 0.00582 -0.0253 0.0289 1.0000
7.750 1.0000 0.01236 0.00610 -0.0245 0.0275 1.0000
8.000 1.0227 0.01265 0.00640 -0.0237 0.0256 1.0000
8.250 1.0449 0.01300 0.00675 -0.0228 0.0234 1.0000
8.500 1.0671 0.01332 0.00710 -0.0219 0.0219 1.0000
8.750 1.0896 0.01359 0.00741 -0.0210 0.0212 1.0000
9.000 1.1116 0.01389 0.00774 -0.0201 0.0198 1.0000
9.250 1.1325 0.01430 0.00811 -0.0190 0.0164 1.0000
9.500 1.1528 0.01476 0.00856 -0.0179 0.0118 1.0000
9.750 1.1703 0.01552 0.00930 -0.0162 0.0056 1.0000
10.000 1.1894 0.01605 0.00988 -0.0149 0.0048 1.0000
10.250 1.2080 0.01661 0.01049 -0.0134 0.0042 1.0000
10.500 1.2262 0.01717 0.01113 -0.0118 0.0037 1.0000
10.750 1.2444 0.01768 0.01170 -0.0103 0.0035 1.0000
11.000 1.2621 0.01820 0.01231 -0.0087 0.0034 1.0000
11.250 1.2791 0.01877 0.01295 -0.0070 0.0032 1.0000
11.500 1.2951 0.01937 0.01364 -0.0052 0.0031 1.0000
11.750 1.3104 0.02001 0.01437 -0.0033 0.0030 1.0000
12.000 1.3248 0.02068 0.01513 -0.0013 0.0028 1.0000
12.250 1.3381 0.02141 0.01595 0.0009 0.0027 1.0000
12.500 1.3503 0.02219 0.01682 0.0032 0.0026 1.0000
12.750 1.3611 0.02303 0.01775 0.0056 0.0025 1.0000
13.000 1.3703 0.02393 0.01875 0.0083 0.0025 1.0000
13.250 1.3754 0.02489 0.01982 0.0115 0.0024 1.0000
13.500 1.3797 0.02600 0.02105 0.0146 0.0023 1.0000
13.750 1.3830 0.02729 0.02249 0.0175 0.0022 1.0000
14.000 1.3843 0.02883 0.02417 0.0203 0.0022 1.0000
14.250 1.3829 0.03064 0.02613 0.0229 0.0021 1.0000
14.500 1.3833 0.03240 0.02802 0.0251 0.0021 1.0000
14.750 1.3833 0.03429 0.03004 0.0269 0.0021 1.0000
15.000 1.3820 0.03640 0.03228 0.0284 0.0021 1.0000
15.250 1.3781 0.03890 0.03491 0.0296 0.0021 1.0000
15.500 1.3710 0.04196 0.03812 0.0302 0.0021 1.0000
15.750 1.3610 0.04574 0.04205 0.0300 0.0020 1.0000
16.000 1.3453 0.05104 0.04752 0.0280 0.0020 1.0000
16.250 1.3214 0.05905 0.05574 0.0230 0.0020 1.0000
16.500 1.2715 0.07454 0.07153 0.0125 0.0021 1.0000
16.750 1.1965 0.09352 0.09075 0.0027 0.0021 1.0000
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