BOEING HSNLF AIRFOIL (bacnlf-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING HSNLF AIRFOIL (bacnlf-il) Reynolds number: 100,000 Max Cl/Cd: 40.45 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bacnlf-il-100000-n5.txt Download as CSV file: xf-bacnlf-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING HSNLF AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5442 0.09251 0.08742 -0.0403 1.0014 0.0184
-9.500 -0.5509 0.08723 0.08220 -0.0429 1.0014 0.0180
-9.250 -0.5617 0.08167 0.07667 -0.0459 1.0014 0.0177
-9.000 -0.5772 0.07699 0.07202 -0.0476 1.0014 0.0175
-8.750 -0.5971 0.07337 0.06840 -0.0474 1.0014 0.0173
-8.500 -0.6194 0.07063 0.06565 -0.0453 1.0014 0.0172
-8.250 -0.6356 0.06738 0.06234 -0.0434 1.0014 0.0169
-8.000 -0.6484 0.06402 0.05887 -0.0414 1.0014 0.0166
-7.750 -0.6577 0.06047 0.05515 -0.0393 1.0014 0.0162
-7.500 -0.6632 0.05671 0.05117 -0.0372 1.0014 0.0157
-7.250 -0.6649 0.05276 0.04694 -0.0351 1.0014 0.0152
-7.000 -0.6627 0.04854 0.04232 -0.0329 1.0014 0.0145
-6.750 -0.6558 0.04443 0.03769 -0.0307 1.0014 0.0138
-6.500 -0.6440 0.04135 0.03418 -0.0289 1.0014 0.0135
-6.250 -0.6298 0.03859 0.03100 -0.0274 1.0014 0.0134
-6.000 -0.6135 0.03593 0.02793 -0.0260 1.0014 0.0133
-5.750 -0.5954 0.03325 0.02484 -0.0249 1.0014 0.0133
-5.500 -0.5754 0.03066 0.02187 -0.0239 1.0014 0.0134
-5.250 -0.5538 0.02832 0.01922 -0.0230 1.0014 0.0137
-5.000 -0.5314 0.02637 0.01705 -0.0222 1.0014 0.0142
-4.750 -0.5085 0.02484 0.01531 -0.0215 1.0014 0.0151
-4.500 -0.4855 0.02373 0.01406 -0.0208 1.0014 0.0175
-4.250 -0.4620 0.02283 0.01297 -0.0201 1.0014 0.0206
-4.000 -0.4394 0.02149 0.01167 -0.0198 1.0014 0.0273
-3.750 -0.4150 0.02021 0.01024 -0.0194 1.0014 0.0331
-3.500 -0.3900 0.01927 0.00921 -0.0192 1.0014 0.0454
-3.250 -0.3636 0.01822 0.00823 -0.0195 1.0014 0.0793
-3.000 -0.3373 0.01553 0.00805 -0.0209 1.0014 0.5922
-2.750 -0.3202 0.01605 0.00869 -0.0177 1.0014 0.6878
-2.500 -0.3009 0.01668 0.00940 -0.0143 0.9984 0.7465
-2.250 -0.2702 0.01679 0.00928 -0.0149 0.9960 0.7586
-2.000 -0.2397 0.01677 0.00907 -0.0158 0.9930 0.7638
-1.750 -0.2079 0.01679 0.00892 -0.0171 0.9901 0.7693
-1.500 -0.1739 0.01683 0.00879 -0.0190 0.9873 0.7749
-1.250 -0.1419 0.01688 0.00871 -0.0202 0.9843 0.7796
-1.000 -0.1113 0.01689 0.00862 -0.0213 0.9802 0.7850
-0.750 -0.0785 0.01695 0.00860 -0.0229 0.9765 0.7901
-0.500 -0.0446 0.01704 0.00864 -0.0246 0.9735 0.7951
-0.250 -0.0140 0.01709 0.00862 -0.0257 0.9695 0.8009
0.000 0.0156 0.01714 0.00867 -0.0265 0.9652 0.8058
0.250 0.0486 0.01723 0.00876 -0.0280 0.9617 0.8116
0.500 0.0808 0.01733 0.00887 -0.0294 0.9582 0.8174
0.750 0.1083 0.01739 0.00898 -0.0298 0.9529 0.8231
1.000 0.1419 0.01749 0.00912 -0.0314 0.9491 0.8298
1.250 0.1721 0.01757 0.00928 -0.0322 0.9443 0.8358
1.500 0.2021 0.01763 0.00942 -0.0331 0.9381 0.8431
1.750 0.2374 0.01769 0.00961 -0.0348 0.9340 0.8496
2.000 0.2628 0.01774 0.00978 -0.0347 0.9262 0.8583
2.250 0.2968 0.01776 0.00995 -0.0361 0.9212 0.8662
2.500 0.3249 0.01770 0.01006 -0.0362 0.9115 0.8756
2.750 0.3583 0.01754 0.01013 -0.0372 0.9019 0.8858
3.000 0.3970 0.01721 0.01003 -0.0389 0.8926 0.8959
3.250 0.4359 0.01617 0.00922 -0.0394 0.8671 0.9061
3.500 0.4675 0.01508 0.00837 -0.0381 0.8295 0.9196
3.750 0.5010 0.01439 0.00789 -0.0379 0.7856 0.9369
4.000 0.5590 0.01382 0.00653 -0.0407 0.5475 0.9385
4.250 0.5746 0.01582 0.00705 -0.0389 0.2588 0.9650
4.500 0.5957 0.01731 0.00785 -0.0387 0.1266 0.9986
4.750 0.6167 0.01835 0.00868 -0.0379 0.0885 0.9986
5.000 0.6382 0.01936 0.00965 -0.0371 0.0667 0.9986
5.250 0.6597 0.02037 0.01064 -0.0363 0.0458 0.9986
5.500 0.6813 0.02144 0.01170 -0.0355 0.0316 0.9986
5.750 0.7025 0.02276 0.01308 -0.0345 0.0249 0.9986
6.000 0.7251 0.02423 0.01472 -0.0337 0.0218 0.9986
6.250 0.7487 0.02588 0.01647 -0.0331 0.0200 0.9986
6.500 0.7735 0.02844 0.01919 -0.0327 0.0188 0.9986
6.750 0.7993 0.03084 0.02192 -0.0321 0.0182 0.9986
7.000 0.8224 0.03361 0.02513 -0.0311 0.0178 0.9986
7.250 0.8416 0.03670 0.02872 -0.0295 0.0176 0.9986
7.500 0.8566 0.04010 0.03263 -0.0275 0.0174 0.9986
7.750 0.8674 0.04374 0.03677 -0.0250 0.0174 0.9986
8.000 0.8743 0.04754 0.04109 -0.0223 0.0172 0.9986
8.250 0.8777 0.05144 0.04544 -0.0194 0.0168 0.9986
8.500 0.8775 0.05545 0.04983 -0.0166 0.0165 0.9986
8.750 0.8737 0.05953 0.05425 -0.0138 0.0161 0.9986
9.000 0.8663 0.06362 0.05860 -0.0112 0.0159 0.9986
9.250 0.8540 0.06754 0.06273 -0.0085 0.0158 0.9986
9.500 0.8385 0.07156 0.06692 -0.0063 0.0159 0.9986
9.750 0.8215 0.07600 0.07149 -0.0054 0.0160 0.9986
10.000 0.8039 0.08114 0.07675 -0.0062 0.0162 0.9986
10.250 0.7878 0.08702 0.08270 -0.0089 0.0167 0.9986
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Polar data table (+)
Polar graphs
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