HQ 1.0/10 AIRFOIL (hq1010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.0/10 AIRFOIL (hq1010-il) Reynolds number: 1,000,000 Max Cl/Cd: 77.99 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1010-il-1000000-n5.txt Download as CSV file: xf-hq1010-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/10 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.9592 0.06267 0.06055 -0.0314 1.0000 0.0022
-13.750 -0.9935 0.05116 0.04883 -0.0404 1.0000 0.0022
-13.500 -1.0159 0.04426 0.04174 -0.0452 1.0000 0.0022
-13.250 -1.0240 0.04033 0.03768 -0.0472 1.0000 0.0022
-13.000 -1.0398 0.03621 0.03336 -0.0482 1.0000 0.0022
-12.750 -1.0572 0.03274 0.02969 -0.0474 1.0000 0.0022
-12.500 -1.0596 0.03106 0.02789 -0.0455 1.0000 0.0022
-12.250 -1.0636 0.02918 0.02584 -0.0427 1.0000 0.0023
-12.000 -1.0584 0.02739 0.02387 -0.0410 1.0000 0.0023
-11.750 -1.0493 0.02579 0.02209 -0.0396 1.0000 0.0023
-11.500 -1.0355 0.02455 0.02072 -0.0384 1.0000 0.0023
-11.250 -1.0216 0.02320 0.01919 -0.0372 1.0000 0.0024
-11.000 -1.0044 0.02215 0.01801 -0.0362 1.0000 0.0024
-10.750 -0.9861 0.02120 0.01694 -0.0354 1.0000 0.0025
-10.500 -0.9679 0.02017 0.01578 -0.0344 1.0000 0.0025
-10.250 -0.9495 0.01911 0.01458 -0.0334 1.0000 0.0026
-10.000 -0.9332 0.01769 0.01299 -0.0322 1.0000 0.0028
-9.750 -0.9125 0.01694 0.01216 -0.0314 1.0000 0.0030
-9.500 -0.8911 0.01629 0.01144 -0.0306 1.0000 0.0032
-9.250 -0.8699 0.01563 0.01071 -0.0297 1.0000 0.0033
-9.000 -0.8482 0.01508 0.01007 -0.0288 1.0000 0.0036
-8.750 -0.8223 0.01447 0.00939 -0.0289 0.9970 0.0038
-8.500 -0.7918 0.01387 0.00871 -0.0299 0.9907 0.0040
-8.250 -0.7597 0.01328 0.00805 -0.0312 0.9845 0.0042
-8.000 -0.7279 0.01276 0.00745 -0.0325 0.9760 0.0044
-7.750 -0.6954 0.01230 0.00693 -0.0337 0.9663 0.0046
-7.500 -0.6652 0.01165 0.00619 -0.0346 0.9524 0.0052
-7.250 -0.6373 0.01124 0.00570 -0.0348 0.9338 0.0059
-6.750 -0.5863 0.01067 0.00495 -0.0340 0.9003 0.0070
-6.500 -0.5608 0.01042 0.00461 -0.0336 0.8872 0.0075
-6.250 -0.5355 0.01008 0.00421 -0.0331 0.8754 0.0092
-6.000 -0.5095 0.00981 0.00389 -0.0328 0.8651 0.0108
-5.750 -0.4833 0.00958 0.00360 -0.0325 0.8559 0.0130
-5.500 -0.4572 0.00932 0.00331 -0.0323 0.8469 0.0169
-5.250 -0.4308 0.00906 0.00307 -0.0321 0.8387 0.0239
-5.000 -0.4039 0.00889 0.00286 -0.0319 0.8307 0.0280
-4.750 -0.3770 0.00869 0.00266 -0.0318 0.8226 0.0333
-4.500 -0.3499 0.00855 0.00248 -0.0317 0.8149 0.0366
-4.250 -0.3229 0.00836 0.00228 -0.0315 0.8067 0.0451
-4.000 -0.2958 0.00818 0.00211 -0.0314 0.7990 0.0552
-3.750 -0.2687 0.00799 0.00195 -0.0313 0.7908 0.0687
-3.500 -0.2416 0.00780 0.00179 -0.0312 0.7827 0.0855
-3.250 -0.2145 0.00762 0.00163 -0.0311 0.7742 0.1053
-3.000 -0.1875 0.00741 0.00149 -0.0310 0.7648 0.1323
-2.750 -0.1605 0.00720 0.00136 -0.0310 0.7560 0.1665
-2.250 -0.1060 0.00683 0.00114 -0.0308 0.7393 0.2317
-2.000 -0.0792 0.00660 0.00103 -0.0308 0.7292 0.2782
-1.750 -0.0534 0.00621 0.00090 -0.0306 0.7169 0.3680
-1.500 -0.0269 0.00596 0.00082 -0.0304 0.7044 0.4320
-1.250 -0.0002 0.00574 0.00076 -0.0303 0.6924 0.4948
-1.000 0.0267 0.00557 0.00074 -0.0301 0.6810 0.5505
-0.750 0.0540 0.00550 0.00073 -0.0300 0.6693 0.5836
-0.500 0.0818 0.00549 0.00072 -0.0300 0.6571 0.6041
-0.250 0.1096 0.00550 0.00071 -0.0299 0.6440 0.6190
0.250 0.1651 0.00553 0.00073 -0.0298 0.6163 0.6476
0.500 0.1929 0.00555 0.00074 -0.0298 0.6029 0.6600
0.750 0.2206 0.00559 0.00077 -0.0297 0.5866 0.6718
1.000 0.2482 0.00564 0.00080 -0.0296 0.5689 0.6850
1.250 0.2755 0.00571 0.00085 -0.0295 0.5475 0.6974
1.500 0.3027 0.00583 0.00089 -0.0294 0.5192 0.7069
1.750 0.3293 0.00602 0.00096 -0.0292 0.4798 0.7151
2.250 0.3823 0.00647 0.00116 -0.0288 0.3991 0.7313
2.750 0.4333 0.00716 0.00146 -0.0282 0.2867 0.7482
3.000 0.4600 0.00733 0.00158 -0.0281 0.2647 0.7571
3.250 0.4868 0.00750 0.00172 -0.0279 0.2457 0.7658
3.750 0.5401 0.00786 0.00200 -0.0276 0.2051 0.7847
4.000 0.5667 0.00802 0.00214 -0.0274 0.1888 0.7944
4.250 0.5931 0.00820 0.00231 -0.0272 0.1713 0.8047
4.500 0.6187 0.00848 0.00250 -0.0269 0.1434 0.8157
4.750 0.6436 0.00881 0.00274 -0.0265 0.1126 0.8271
5.000 0.6686 0.00910 0.00298 -0.0260 0.0908 0.8396
5.250 0.6934 0.00939 0.00322 -0.0256 0.0711 0.8536
5.500 0.7180 0.00963 0.00348 -0.0250 0.0580 0.8719
5.750 0.7420 0.00981 0.00372 -0.0243 0.0484 0.8996
6.000 0.7706 0.00999 0.00399 -0.0245 0.0402 0.9553
6.250 0.8072 0.01035 0.00432 -0.0267 0.0300 1.0000
6.500 0.8321 0.01069 0.00462 -0.0263 0.0234 1.0000
6.750 0.8569 0.01104 0.00496 -0.0259 0.0175 1.0000
7.000 0.8815 0.01142 0.00531 -0.0255 0.0128 1.0000
7.250 0.9058 0.01182 0.00569 -0.0250 0.0091 1.0000
7.500 0.9299 0.01224 0.00611 -0.0245 0.0058 1.0000
7.750 0.9539 0.01267 0.00654 -0.0240 0.0046 1.0000
8.000 0.9779 0.01310 0.00700 -0.0235 0.0040 1.0000
8.250 1.0015 0.01356 0.00750 -0.0229 0.0035 1.0000
8.500 1.0251 0.01399 0.00800 -0.0223 0.0033 1.0000
8.750 1.0484 0.01446 0.00852 -0.0217 0.0031 1.0000
9.000 1.0712 0.01497 0.00909 -0.0211 0.0029 1.0000
9.250 1.0935 0.01550 0.00969 -0.0204 0.0027 1.0000
9.500 1.1152 0.01610 0.01035 -0.0196 0.0025 1.0000
9.750 1.1364 0.01672 0.01103 -0.0187 0.0024 1.0000
10.000 1.1569 0.01739 0.01178 -0.0178 0.0024 1.0000
10.250 1.1759 0.01819 0.01266 -0.0167 0.0022 1.0000
10.500 1.1925 0.01920 0.01381 -0.0153 0.0020 1.0000
10.750 1.2057 0.02047 0.01523 -0.0135 0.0019 1.0000
11.000 1.2225 0.02129 0.01614 -0.0121 0.0019 1.0000
11.250 1.2403 0.02195 0.01687 -0.0110 0.0018 1.0000
11.500 1.2538 0.02293 0.01795 -0.0093 0.0018 1.0000
11.750 1.2651 0.02386 0.01898 -0.0073 0.0018 1.0000
12.000 1.2697 0.02502 0.02027 -0.0043 0.0018 1.0000
12.250 1.2770 0.02601 0.02136 -0.0019 0.0017 1.0000
12.500 1.2819 0.02722 0.02268 0.0005 0.0017 1.0000
12.750 1.2819 0.02887 0.02447 0.0029 0.0017 1.0000
13.000 1.2896 0.03004 0.02571 0.0044 0.0017 1.0000
13.250 1.2897 0.03190 0.02772 0.0060 0.0017 1.0000
13.500 1.2887 0.03401 0.02997 0.0073 0.0016 1.0000
13.750 1.2876 0.03628 0.03237 0.0083 0.0016 1.0000
14.000 1.2790 0.03951 0.03576 0.0088 0.0016 1.0000
14.250 1.2724 0.04280 0.03920 0.0087 0.0016 1.0000
14.500 1.2658 0.04637 0.04291 0.0081 0.0016 1.0000
14.750 1.2534 0.05102 0.04771 0.0066 0.0016 1.0000
15.000 1.2417 0.05603 0.05287 0.0045 0.0016 1.0000
15.250 1.2284 0.06173 0.05872 0.0016 0.0016 1.0000
15.500 1.2019 0.07036 0.06753 -0.0033 0.0016 1.0000
15.750 1.1809 0.07881 0.07614 -0.0084 0.0016 1.0000
16.000 1.1598 0.08782 0.08530 -0.0138 0.0016 1.0000
16.250 1.1373 0.09732 0.09492 -0.0192 0.0016 1.0000
16.500 1.0953 0.11120 0.10896 -0.0271 0.0017 1.0000
16.750 1.0656 0.12270 0.12057 -0.0335 0.0017 1.0000
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