HQ 1.5/8 AIRFOIL (hq158-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/8 AIRFOIL (hq158-il) Reynolds number: 500,000 Max Cl/Cd: 86.77 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq158-il-500000.txt Download as CSV file: xf-hq158-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5024 0.08240 0.08021 -0.0209 1.0000 0.0146
-8.250 -0.5047 0.07803 0.07588 -0.0236 1.0000 0.0149
-8.000 -0.5098 0.07358 0.07148 -0.0265 1.0000 0.0151
-7.750 -0.5168 0.06817 0.06609 -0.0324 1.0000 0.0148
-7.500 -0.5180 0.06253 0.06039 -0.0370 1.0000 0.0150
-7.250 -0.5164 0.05739 0.05515 -0.0398 1.0000 0.0154
-7.000 -0.5118 0.05260 0.05024 -0.0413 1.0000 0.0160
-6.750 -0.5038 0.04819 0.04566 -0.0417 1.0000 0.0168
-6.500 -0.4846 0.04624 0.04350 -0.0408 1.0000 0.0181
-6.250 -0.4768 0.04308 0.04013 -0.0396 1.0000 0.0182
-6.000 -0.4709 0.04011 0.03695 -0.0376 1.0000 0.0183
-5.750 -0.4598 0.03686 0.03345 -0.0365 0.9992 0.0183
-5.250 -0.4058 0.01982 0.01492 -0.0404 0.9906 0.0112
-5.000 -0.3720 0.01788 0.01270 -0.0416 0.9871 0.0109
-4.750 -0.3403 0.01413 0.00849 -0.0425 0.9842 0.0117
-4.500 -0.3052 0.01267 0.00687 -0.0442 0.9819 0.0129
-4.250 -0.2726 0.01214 0.00630 -0.0454 0.9770 0.0152
-4.000 -0.2388 0.01101 0.00505 -0.0466 0.9730 0.0158
-3.750 -0.2038 0.01021 0.00414 -0.0481 0.9695 0.0178
-3.500 -0.1733 0.00935 0.00319 -0.0485 0.9626 0.0255
-3.250 -0.1415 0.00875 0.00270 -0.0494 0.9567 0.0621
-3.000 -0.1125 0.00832 0.00240 -0.0498 0.9485 0.1063
-2.750 -0.0860 0.00736 0.00209 -0.0501 0.9406 0.2805
-2.500 -0.0640 0.00637 0.00192 -0.0494 0.9298 0.5164
-2.250 -0.0388 0.00612 0.00185 -0.0486 0.9190 0.5939
-2.000 -0.0130 0.00600 0.00177 -0.0479 0.9076 0.6377
-1.750 0.0128 0.00593 0.00168 -0.0472 0.8960 0.6689
-1.500 0.0387 0.00587 0.00164 -0.0465 0.8856 0.7000
-1.250 0.0646 0.00582 0.00162 -0.0459 0.8751 0.7273
-1.000 0.0906 0.00579 0.00160 -0.0453 0.8650 0.7518
-0.750 0.1161 0.00576 0.00158 -0.0445 0.8543 0.7787
-0.500 0.1418 0.00574 0.00155 -0.0438 0.8427 0.7985
-0.250 0.1678 0.00572 0.00153 -0.0431 0.8322 0.8173
0.000 0.1937 0.00567 0.00151 -0.0425 0.8216 0.8358
0.250 0.2196 0.00562 0.00148 -0.0419 0.8103 0.8531
0.500 0.2457 0.00558 0.00145 -0.0414 0.7991 0.8699
0.750 0.2717 0.00551 0.00142 -0.0407 0.7880 0.8900
1.000 0.2995 0.00545 0.00141 -0.0405 0.7770 0.9182
1.250 0.3384 0.00542 0.00141 -0.0428 0.7646 0.9560
1.500 0.3817 0.00544 0.00141 -0.0462 0.7509 0.9970
1.750 0.4092 0.00551 0.00142 -0.0462 0.7357 1.0000
2.000 0.4352 0.00559 0.00146 -0.0458 0.7187 1.0000
2.250 0.4611 0.00569 0.00149 -0.0453 0.6981 1.0000
2.500 0.4869 0.00581 0.00156 -0.0449 0.6726 1.0000
2.750 0.5122 0.00597 0.00162 -0.0443 0.6406 1.0000
3.000 0.5371 0.00619 0.00169 -0.0437 0.5955 1.0000
3.250 0.5607 0.00655 0.00180 -0.0429 0.5313 1.0000
3.500 0.5835 0.00707 0.00198 -0.0420 0.4519 1.0000
3.750 0.6073 0.00754 0.00224 -0.0414 0.3893 1.0000
4.000 0.6310 0.00805 0.00248 -0.0409 0.3246 1.0000
4.250 0.6551 0.00854 0.00280 -0.0403 0.2921 1.0000
4.500 0.6804 0.00888 0.00302 -0.0400 0.2456 1.0000
4.750 0.7049 0.00933 0.00331 -0.0396 0.2063 1.0000
5.500 0.7741 0.01132 0.00458 -0.0379 0.0557 1.0000
5.750 0.7984 0.01184 0.00505 -0.0374 0.0408 1.0000
6.000 0.8226 0.01235 0.00554 -0.0368 0.0288 1.0000
6.250 0.8451 0.01323 0.00637 -0.0359 0.0130 1.0000
6.500 0.8659 0.01441 0.00773 -0.0345 0.0105 1.0000
6.750 0.8877 0.01537 0.00885 -0.0335 0.0098 1.0000
7.000 0.9093 0.01633 0.00993 -0.0324 0.0090 1.0000
7.250 0.9328 0.01689 0.01054 -0.0319 0.0079 1.0000
7.500 0.9538 0.01791 0.01165 -0.0308 0.0073 1.0000
7.750 0.9730 0.01932 0.01320 -0.0296 0.0068 1.0000
8.000 0.9879 0.02196 0.01611 -0.0277 0.0064 1.0000
8.250 1.0010 0.02555 0.02010 -0.0256 0.0061 1.0000
8.500 1.0167 0.02797 0.02283 -0.0240 0.0060 1.0000
8.750 1.0274 0.03118 0.02642 -0.0219 0.0060 1.0000
9.000 1.0273 0.03634 0.03204 -0.0190 0.0062 1.0000
9.250 1.0400 0.03798 0.03386 -0.0175 0.0063 1.0000
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